CA2056474A1 - Combustor dome - Google Patents
Combustor domeInfo
- Publication number
- CA2056474A1 CA2056474A1 CA002056474A CA2056474A CA2056474A1 CA 2056474 A1 CA2056474 A1 CA 2056474A1 CA 002056474 A CA002056474 A CA 002056474A CA 2056474 A CA2056474 A CA 2056474A CA 2056474 A1 CA2056474 A1 CA 2056474A1
- Authority
- CA
- Canada
- Prior art keywords
- coolant
- apertures
- leg
- dome
- combustor
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/10—Air inlet arrangements for primary air
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
- F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/20—Heat transfer, e.g. cooling
- F05B2260/202—Heat transfer, e.g. cooling by film cooling
Abstract
Patent 13LN-1969 ABSTRACT
A combustor dome includes an annular dome plate having a plurality of circumferentially spaced apertures in a central portion thereof for receiving a plurality of carburetors. The dome plate also includes outer and inner support portions for joining the dome plate to combustion liners. Each of the support portions include a first leg extending from the central portion, a second leg, and an arcuate apex joining the first and second legs. The apex has a uniform thickness and includes a plurality of circumferentially spaced coolant apertures for channeling cooling air therethrough.
A combustor dome includes an annular dome plate having a plurality of circumferentially spaced apertures in a central portion thereof for receiving a plurality of carburetors. The dome plate also includes outer and inner support portions for joining the dome plate to combustion liners. Each of the support portions include a first leg extending from the central portion, a second leg, and an arcuate apex joining the first and second legs. The apex has a uniform thickness and includes a plurality of circumferentially spaced coolant apertures for channeling cooling air therethrough.
Description
i3 ~ r~
-1- 2atent 13LN-1969 CO~ TO~ DOM~
The U.S. Government has rights in this invention pursuant to Contract No. S8BOOlL awarded by the Department of the Navy.
Techpica1 Field The present invention relate; generally to gas turbine engin s, and, more specifically, to a combustor dome at an upstrea~ end of an annular combustor.
Back~round Art A conventional gas turbine engine combustor includes a plurality of circumferentially spaced carburetors disposed in a dome at an upstream end of the combustor. The carburetors receive compressed air from a compressor disposed upstream therefrom and fuel for forming a fuel/air mixtur~ which is ignited ~or forming combustion gases in ~he conbustor which are then channeled to a conventional turbine disposed downstr~am therefrom. Maintaining stable combustion and achieving good performance of the combustor requires co~trolled introduction of the compressed air and good mixing in the combustor for obtaining preferred temperature profiles of the combustion gases di charged from the combustor. One of the most important influencing factors on the temperature distribution of ~he combustion gases discharged from the combustor is the uniformity and stability of the fuel and air in the combustor dome region, which is conventionally referred to as the primary zone.
Furthermore, a portion of the compressed air must also be effectively used for cooling the components o~ the combustor including the combustor dome and the combustion liners joined thereto. The compressed air used for cooling is typically channeled through machined cooling nuggets having circumferential slots for spreading the cooling air -2- ?atent 13LN-1969 over the liners for obtaining acceptable film cooling thereof. The cooling nuggets are machin~d structures to ensure that small tolerances are maintained for providing effective cooling. Relatively small variations in the s con~igurations of the cooling nuggets can significantly affect the cooling ability of the cooling nuggets. However, combustor domes having machined cool.ing nuggets are relatively complex and expensive to manu~Eacture.
Obiects of the Inventio~
Accordingly, one object of the present invention i5 to provide a new and improved co~bustor dome for a ga~
turbine engine combustor.
Another object of the present invention is to provide a combustor dome having cooling air apertures therein, and simply fabricated without the need for complex machining.
Disclosure of_Invention A combustor dome includes an annular dome plate having a plurality of circumferentially spaced apertures in a central portion thereof for receiving a plurality of carburetors. The dome plate also includes outer and inner support portions for joinin~ the dome plate to combustion liners. Each of the support portions includes a first leg extending from the central portion, a second leg, and an arcuate apex joining the first and second legs. The apex has a uniform thickness and includes a plurality of circu~erentially spaced coolant apertures for channeling cooling air therethrough.
Brief Description of Drawinqs The novel features believed characteristic o~ the invention are set forth and di~ferentiated in the claims, c3 ~ ~ ~ r~
_3_ Patent 13LN-1969 The inven~ion, in accordance with preferred and exemplary embodiments, together with further objects and advantages thereof, is more particularly described in the following detailed description taken in conjunction with the accompanying drawing in which:
Figure 1 is a longitudinal sectional view of a portion o~ an annular combustor incl~ding a combustor dome in accordance with one e~bodiment of the present invention.
Figure 2 is an upstream facing view of a portion of the annular dome plate of the combustor dome illustrated in Figure 1.
Figure 3 is an enlarged lo~gitudinal sectional view o~ a radially inner support portion of tha combustor dome illustrated in Fi~ure 1.
Figure 4 is a perspective view of a portion of the combustion dome illustrated in Figure 1.
Fi~ure 5 is a longitudinal sectional view of the inner support portion of the combustor dome illustrated in Figure 1 in accordance with an alternate ~mbodiment of the present i~v~ntion.
Mode(s~ For carrYina Out the Invention Illustrated in Figure 1 is a longitudinal sectional view of an annular combustor 10 disposed coaxially about an axial centerline axis 12 inside an annular casing 2S 14 of a gas turbine engine. The co~bustor 10 includes an annular radially outer combustion liner 16, and an a~lular radially inner combustion liner 18 spaced therefrom to define an annular combustion chamber 20. The combustor 10 also includes a combustor dome, indicated generally at 22, shown in accordance with one embodiment of the present invention. The dome 22 includes an annular dome plate 24 disposed coaxially about the axial centerline axis 12 and fixedly joined to upstream ends 16a, 18a of the outer and inner liners 16, 18, respectively, by p}uralities Qf ~ t _4_ Patent 13L~-1969 circumferentially spaced bolts 26.
Conventionally joined to the dome plate 24 is a plurality o~ circumferentially spaced conventional carburetors 28, each lncluding a conventional fuel injector 30 and air swirler 32. Al~o joined by the bolts 26 to the combustion liner upstream ends 16a, 18a, are conventional outer and inner sheet metal cowls 34 and 36 which conventionally channel compressed air 38 from a compressor (not shown) disposed upstream of the co~bustor 10. A
portion of the compressed air 38 is mixed with fuel from the injector 30 and conventionally ignit~d for forming com~ustion gases 40 in the chamber 20. The combustion gases 40 are discharged from an outlet 42 at thP downstream end of the combustor 10 and suitably channeled to a turbine (not shown) disposed downstream from the combustor 10.
In order to cool the liners 16 and 18, each of the liners includes a plurality of rows of circumferentially spaced inclined cooling holes 44, also referred to as multiholes 44, which receive a portion of the compressed air 38 channeled over the liners 16 and 18, which air 38 flows through the multiholes 44 in the liners 16 and lB toward and into the chamber 20 for formin~ a film cooling bounda~y layer 46 along the inside surfaces of the liners 16, 18 for protecting the liners from the combustion gases 40. A first row 44a of the cooling holes 44 is preferably spaced relatively closely to the dome plate 24 for beginning the boundary layer 46 as soon as possible in the combustion chamber 20. Portions 40a of the combustion gases 40 recirculate immediately downstream of the carburetors 28 adjacent to the dome plate 24 and the liner upstream ends 16a, 18a. Accordingly, a conventional annular baffle, or splashplate, 48 conventionally supports the carburetor 28 to the dome plate 24 for protecting in part the dome plate 24 from the hot combustion gases 40a.
Referring to Figures 2-4, the combustor dome 22 in accordance with a preferred embodiment of the present invention is shown in more detail. The dome plate. 24 is _5_ Patent 13LN-196 preferably a unitary member having a substantially constant thickness T, which is preferably obtained by forming the dome plate 24 as a sheet metal member. In this way, the dome plate 24 may be fabricated using conYentional sheet S metal stamping and punching methods for forming a single member without the need for joininy, by we.Lding for example, several components to form the dome plate 24 as is conven~ionally done in the prior art. Furthermore, utilizing a sheet metal dome plate 24 also eliminates the 10 . relatively expen~ive machining operations, such as lathe turning, used on members not having a uniform thickness. As described hereinbelow, the various apertures in the dome plate 24 may be formed by conventional punching and electrical discharge machining (EDM).
As illustrated in Figure 2, the dome plate 24 includes an annular central portion 50 disposed coaxially about the centerline axis 12 which includes a plurality of circumferentially spaced apertures 52 for receiving respective ones of the carburetors 28. The central portion apertures 52 may be formed by simply punching holes through the central portion 50 using conventional methods. The dome plate 24 further includes annular, radially outer and inner support portions 54 and 56, respectively, which extend integrally from the central portion 50 for joining the do~e plate 24 to the co~bustion liners 16, 18. The preferred configuration of the outer and inner support portions 54, 56 as described hereinbelow may also be formed by conventional stamping or bending of the dome plate 24.
Each of the support portions 54, 56 includes a first leg 58 extending from the central portion 50, a second leg 60, and an arcuate apex 62 .integrally joining the first leg 58 to the second leg 60. The apex 62 has the same uniform thickness T as the remainder of the dome plate 24 and includes a plurality of coolant apertures 64 which are circumferentially spaced and aligned at a common radius from the centerline axis 12 for channeling cooling air therethrough. The second legs 60 each include a plurality r~
-6- Patent 13LN-1969 of circumferentially spaced holes 66 through which are positioned the bolts 26 for mounting the dome plate 24 to the liners 16, 18.
Since the outer and inner support portions 54 and 56 are substantially identical, the inner support portion 5S
will be described in more detail, it being understood that the same deæcription also applies to the outer support portion 54. Figure 3 illustrates in more particularity the inner support portion 56 conventionally joined to the baffle 48, swirler 32, inner cowl 36, and inner combustio~ liner 18. In the preferred embodiment, the first and second legs 58, 60 are straight, and the second leg 60 is spaced from the first leg 58 for joining the do~e plate 24 to the inner combustion linsr 18. Each of the coolant apertures 64 has a central longitudinal axis 68 disposed at an acute angle A
relative to the second les 60 for channeling a portion of the compressed air 38 as a coolant through the aperture 64 in an outward direction relative to the central portio~
apertures 52 for impinging the coolant 38 on the inner surface of the combustion liner 18 at about the acute angle A. The longitudinal axis 68 of the aperture 64 is also disposed generally parallel to the fixst leg 58 so that tha coolant 38 is channeled thxough the aperture 64 generally parallel the first leq 58.
The apex 62 may be conventionally formed by a stamping or bending operation of the dome plate 24 for creating a concave inner surface of radius R and a co~ple~entary convex outer surface which has a radius R plus the thickness T. The coolant apertures 64 may be formed in the apsx 62 by conventional EDM, and, similarly, the holes 66 may also be formed ~y EDM.
The resulting configuration of the coolant aperture 64 in the apex 62 causes the coolant 38 to impinge against the combustion liner upstream end (16a, 18a~ for both cooling that portion of the liner and, for initiating the boundary layer 46 from the inclined cooling holes i.e.
at the first row of cooling holes 44a. In a preferred _7_ Patent 13LN-1969 embodiment of the present invention, the first row 44a o~
the cooling holes 44 is predeterminedly spaced downstream from the coolant apertures 64 at a distance L so that the coolant apertures 64 form a coolant boundary layer to initiate the film cooling from the inclined cooling holes first row 44a.
A9 illustrated in more particularity in Figure 4, the coolant apertures 64 are predeterminedly circumferentially spaced apart a distance!S for providing a substantially uniform boundary layer of the coolant 38 between the apertures 64 and the first row 44a of the cooling holes 44 for providing film cooling of the co~bustion liners (16, 18). Each o~ the apertures 64 has a diameter D, and in one exemplary embodiment o~ the present lS invention the coolant apertures 64 are circumferentially spaced apart at a distanc~ S which is about twice the dlameter D. In this way, the coolant apertures 64 cooperate with each other in ths arcuate apex 62 and with the liner upstr am ~nds (16a, 18a) between the apertur~s 64 and the first row 44a o~ cooling holes 44 for providing an effective, substantially uniform boundary layer of coolant 38.
Component test~ conducted on this preferred embodiment of the invention indicate the formation of effective film cooling wi~hout the need for conventional cooling nugget structure having film cooling slots. More specifically, both the outer and inner support portions 54 and 56 are characterized by the absence of structure such as a cooling nugget lip for forming an annular plenum for receivin~ the coolant 38 from the coolant apertures 64 to for~ a boundary layer. In the prior art, a film cooling boundary layer is typically formed by cooling holes feeding an annular U-shaped plenum having an annular outlet slot to form a substantially uniform film cooling boundary layer therefro~. However, in accordance with the preferrad e~bodiment of the present invention as described above, the coolant apertures 64 disposed simply in the arcuate apex 62 8 Patent 13L~-1969 are effective for cooling the co~bustor liner upstream ends (16a, 18a) without the need for a conventional cooling nugget structure.
As shown in Figure 3, the baffles 48 are conventional and are conventionally joined to the central portion apertures 52 and spaced at least in part from the first legs 58 for forming a channel 70 therebetween.
Conventional impingement-type cooling holes 72 are conventionally formed through the first leg 58 to impinge the coolant 38 against the back side of the baffle 48 and then flow generally parallel along the sur~ace of the first leg 58 in the channel 70. The coolant ~rom khe channel 70 then flows over the apex 62 and is disposed between the coolant 38 from the apertures 64 and the combustion gases 40. It is believed that this cooperation of the coolant 38 from the channel 70 assists in providing film cooling by the coolant 38 from the apertures 64 against the liner upstrea~
ends 16a, 18a.
Since the dome plate 24 may be formed ~rom a unitary sheet metal ~ember and conventionally formed using stamping, bending, punching, and EDM operations, ~he dome plate 24 ~ay be more easily manufactured at reduced cost as co~pared to multi-piece dome plates of varying thicknes~
which require more expensive machining operations including the use of lathes, for example. Furthermore, since the dome plate 24 may be simply bolted to the outer and inner liners 16.and 18, the fabrication mPthod for the entire combustor dome 22 is simplified, which also reduces cost, and allows for relatively easy disassembly and repair and replacement of component parts thereof.
Illustrated in Figure 5 is an alternate embodiment of the present invention wherein each of the outer and inner support portions 54, 56 (inner support portion 56 being shown) may additionally include an annular ring 74 suitably conventionally fixedly connected to the concave side of the apex 62, ~or example by brazing. The coolant aper~ure 64 may then be ~ormed through both the apex 62 and through the ~d r~ J
_9_ Patent 13L~-1969 ring 74 coaxially about the longitudinal axis 68. In this way, a relatively long coolant aperture 64, i.e. longer than the thickness T of the dome plate 24, may be provided for more accurately directing the coolant 38 to impinge against 5 the liners 16, 18. The coolant apertures 64 may, therefore, have a relatively high length-to-diameter ratio as is typically found in a conventional, machined cooling nugget for more accurately directing the coolant ~8 for ensuring the formation of a substantially uniform film cooling boundary layer.
In the preferred embodiment of the invention disclosed above, the outer and inner support portions 54 and 56 including the coolant apertures 64 have been shown by tests to be effective for suitably cooling the combustor liners 16, 18 disposed adjacent to the apertures 64, and for initiating the film cooling boundary layer from the first row 44a of the inclined holes 44. In one embodiment of the inventi~n, the spacing L between the coolant apertures 64 and the first row 44a o~ inclined holes is about 0.5 inches (12.7 mm). The acute angles A for the outer and inner support portions 54, 56 are 54 and 44, respectively. The inclined holes 44 are inclined at about an angle of 20 relative to the liners 16, 18 and have a pitch-to-diameter ratio of about 6.
In alternate embodiments of the present invention, the outer and inner support portions 54 and 56 may be utilized with conventional film cooling nuggets formed in the liners 16, 18 instead of using the inclined apertures, or ~ultiholes, 44. However, it is preferred that the first row of film cooling nuggets is spaced as close as practical to the coolant apertures 64 for ensuring effective cooling of the liners at that location.
While there have been described herein what are considered to be preferred embodiments of the present invention, other modifications of the invention shall be apparent to those skilled in the art from the teachings herein, and it is, therefore, desired to be secured in the ~3~ ~ ~?~
-10- Patent 13LN-1969 appended claims all such modiflcations as fall within the true spirit and scope of the invention.
-1- 2atent 13LN-1969 CO~ TO~ DOM~
The U.S. Government has rights in this invention pursuant to Contract No. S8BOOlL awarded by the Department of the Navy.
Techpica1 Field The present invention relate; generally to gas turbine engin s, and, more specifically, to a combustor dome at an upstrea~ end of an annular combustor.
Back~round Art A conventional gas turbine engine combustor includes a plurality of circumferentially spaced carburetors disposed in a dome at an upstream end of the combustor. The carburetors receive compressed air from a compressor disposed upstream therefrom and fuel for forming a fuel/air mixtur~ which is ignited ~or forming combustion gases in ~he conbustor which are then channeled to a conventional turbine disposed downstr~am therefrom. Maintaining stable combustion and achieving good performance of the combustor requires co~trolled introduction of the compressed air and good mixing in the combustor for obtaining preferred temperature profiles of the combustion gases di charged from the combustor. One of the most important influencing factors on the temperature distribution of ~he combustion gases discharged from the combustor is the uniformity and stability of the fuel and air in the combustor dome region, which is conventionally referred to as the primary zone.
Furthermore, a portion of the compressed air must also be effectively used for cooling the components o~ the combustor including the combustor dome and the combustion liners joined thereto. The compressed air used for cooling is typically channeled through machined cooling nuggets having circumferential slots for spreading the cooling air -2- ?atent 13LN-1969 over the liners for obtaining acceptable film cooling thereof. The cooling nuggets are machin~d structures to ensure that small tolerances are maintained for providing effective cooling. Relatively small variations in the s con~igurations of the cooling nuggets can significantly affect the cooling ability of the cooling nuggets. However, combustor domes having machined cool.ing nuggets are relatively complex and expensive to manu~Eacture.
Obiects of the Inventio~
Accordingly, one object of the present invention i5 to provide a new and improved co~bustor dome for a ga~
turbine engine combustor.
Another object of the present invention is to provide a combustor dome having cooling air apertures therein, and simply fabricated without the need for complex machining.
Disclosure of_Invention A combustor dome includes an annular dome plate having a plurality of circumferentially spaced apertures in a central portion thereof for receiving a plurality of carburetors. The dome plate also includes outer and inner support portions for joinin~ the dome plate to combustion liners. Each of the support portions includes a first leg extending from the central portion, a second leg, and an arcuate apex joining the first and second legs. The apex has a uniform thickness and includes a plurality of circu~erentially spaced coolant apertures for channeling cooling air therethrough.
Brief Description of Drawinqs The novel features believed characteristic o~ the invention are set forth and di~ferentiated in the claims, c3 ~ ~ ~ r~
_3_ Patent 13LN-1969 The inven~ion, in accordance with preferred and exemplary embodiments, together with further objects and advantages thereof, is more particularly described in the following detailed description taken in conjunction with the accompanying drawing in which:
Figure 1 is a longitudinal sectional view of a portion o~ an annular combustor incl~ding a combustor dome in accordance with one e~bodiment of the present invention.
Figure 2 is an upstream facing view of a portion of the annular dome plate of the combustor dome illustrated in Figure 1.
Figure 3 is an enlarged lo~gitudinal sectional view o~ a radially inner support portion of tha combustor dome illustrated in Fi~ure 1.
Figure 4 is a perspective view of a portion of the combustion dome illustrated in Figure 1.
Fi~ure 5 is a longitudinal sectional view of the inner support portion of the combustor dome illustrated in Figure 1 in accordance with an alternate ~mbodiment of the present i~v~ntion.
Mode(s~ For carrYina Out the Invention Illustrated in Figure 1 is a longitudinal sectional view of an annular combustor 10 disposed coaxially about an axial centerline axis 12 inside an annular casing 2S 14 of a gas turbine engine. The co~bustor 10 includes an annular radially outer combustion liner 16, and an a~lular radially inner combustion liner 18 spaced therefrom to define an annular combustion chamber 20. The combustor 10 also includes a combustor dome, indicated generally at 22, shown in accordance with one embodiment of the present invention. The dome 22 includes an annular dome plate 24 disposed coaxially about the axial centerline axis 12 and fixedly joined to upstream ends 16a, 18a of the outer and inner liners 16, 18, respectively, by p}uralities Qf ~ t _4_ Patent 13L~-1969 circumferentially spaced bolts 26.
Conventionally joined to the dome plate 24 is a plurality o~ circumferentially spaced conventional carburetors 28, each lncluding a conventional fuel injector 30 and air swirler 32. Al~o joined by the bolts 26 to the combustion liner upstream ends 16a, 18a, are conventional outer and inner sheet metal cowls 34 and 36 which conventionally channel compressed air 38 from a compressor (not shown) disposed upstream of the co~bustor 10. A
portion of the compressed air 38 is mixed with fuel from the injector 30 and conventionally ignit~d for forming com~ustion gases 40 in the chamber 20. The combustion gases 40 are discharged from an outlet 42 at thP downstream end of the combustor 10 and suitably channeled to a turbine (not shown) disposed downstream from the combustor 10.
In order to cool the liners 16 and 18, each of the liners includes a plurality of rows of circumferentially spaced inclined cooling holes 44, also referred to as multiholes 44, which receive a portion of the compressed air 38 channeled over the liners 16 and 18, which air 38 flows through the multiholes 44 in the liners 16 and lB toward and into the chamber 20 for formin~ a film cooling bounda~y layer 46 along the inside surfaces of the liners 16, 18 for protecting the liners from the combustion gases 40. A first row 44a of the cooling holes 44 is preferably spaced relatively closely to the dome plate 24 for beginning the boundary layer 46 as soon as possible in the combustion chamber 20. Portions 40a of the combustion gases 40 recirculate immediately downstream of the carburetors 28 adjacent to the dome plate 24 and the liner upstream ends 16a, 18a. Accordingly, a conventional annular baffle, or splashplate, 48 conventionally supports the carburetor 28 to the dome plate 24 for protecting in part the dome plate 24 from the hot combustion gases 40a.
Referring to Figures 2-4, the combustor dome 22 in accordance with a preferred embodiment of the present invention is shown in more detail. The dome plate. 24 is _5_ Patent 13LN-196 preferably a unitary member having a substantially constant thickness T, which is preferably obtained by forming the dome plate 24 as a sheet metal member. In this way, the dome plate 24 may be fabricated using conYentional sheet S metal stamping and punching methods for forming a single member without the need for joininy, by we.Lding for example, several components to form the dome plate 24 as is conven~ionally done in the prior art. Furthermore, utilizing a sheet metal dome plate 24 also eliminates the 10 . relatively expen~ive machining operations, such as lathe turning, used on members not having a uniform thickness. As described hereinbelow, the various apertures in the dome plate 24 may be formed by conventional punching and electrical discharge machining (EDM).
As illustrated in Figure 2, the dome plate 24 includes an annular central portion 50 disposed coaxially about the centerline axis 12 which includes a plurality of circumferentially spaced apertures 52 for receiving respective ones of the carburetors 28. The central portion apertures 52 may be formed by simply punching holes through the central portion 50 using conventional methods. The dome plate 24 further includes annular, radially outer and inner support portions 54 and 56, respectively, which extend integrally from the central portion 50 for joining the do~e plate 24 to the co~bustion liners 16, 18. The preferred configuration of the outer and inner support portions 54, 56 as described hereinbelow may also be formed by conventional stamping or bending of the dome plate 24.
Each of the support portions 54, 56 includes a first leg 58 extending from the central portion 50, a second leg 60, and an arcuate apex 62 .integrally joining the first leg 58 to the second leg 60. The apex 62 has the same uniform thickness T as the remainder of the dome plate 24 and includes a plurality of coolant apertures 64 which are circumferentially spaced and aligned at a common radius from the centerline axis 12 for channeling cooling air therethrough. The second legs 60 each include a plurality r~
-6- Patent 13LN-1969 of circumferentially spaced holes 66 through which are positioned the bolts 26 for mounting the dome plate 24 to the liners 16, 18.
Since the outer and inner support portions 54 and 56 are substantially identical, the inner support portion 5S
will be described in more detail, it being understood that the same deæcription also applies to the outer support portion 54. Figure 3 illustrates in more particularity the inner support portion 56 conventionally joined to the baffle 48, swirler 32, inner cowl 36, and inner combustio~ liner 18. In the preferred embodiment, the first and second legs 58, 60 are straight, and the second leg 60 is spaced from the first leg 58 for joining the do~e plate 24 to the inner combustion linsr 18. Each of the coolant apertures 64 has a central longitudinal axis 68 disposed at an acute angle A
relative to the second les 60 for channeling a portion of the compressed air 38 as a coolant through the aperture 64 in an outward direction relative to the central portio~
apertures 52 for impinging the coolant 38 on the inner surface of the combustion liner 18 at about the acute angle A. The longitudinal axis 68 of the aperture 64 is also disposed generally parallel to the fixst leg 58 so that tha coolant 38 is channeled thxough the aperture 64 generally parallel the first leq 58.
The apex 62 may be conventionally formed by a stamping or bending operation of the dome plate 24 for creating a concave inner surface of radius R and a co~ple~entary convex outer surface which has a radius R plus the thickness T. The coolant apertures 64 may be formed in the apsx 62 by conventional EDM, and, similarly, the holes 66 may also be formed ~y EDM.
The resulting configuration of the coolant aperture 64 in the apex 62 causes the coolant 38 to impinge against the combustion liner upstream end (16a, 18a~ for both cooling that portion of the liner and, for initiating the boundary layer 46 from the inclined cooling holes i.e.
at the first row of cooling holes 44a. In a preferred _7_ Patent 13LN-1969 embodiment of the present invention, the first row 44a o~
the cooling holes 44 is predeterminedly spaced downstream from the coolant apertures 64 at a distance L so that the coolant apertures 64 form a coolant boundary layer to initiate the film cooling from the inclined cooling holes first row 44a.
A9 illustrated in more particularity in Figure 4, the coolant apertures 64 are predeterminedly circumferentially spaced apart a distance!S for providing a substantially uniform boundary layer of the coolant 38 between the apertures 64 and the first row 44a of the cooling holes 44 for providing film cooling of the co~bustion liners (16, 18). Each o~ the apertures 64 has a diameter D, and in one exemplary embodiment o~ the present lS invention the coolant apertures 64 are circumferentially spaced apart at a distanc~ S which is about twice the dlameter D. In this way, the coolant apertures 64 cooperate with each other in ths arcuate apex 62 and with the liner upstr am ~nds (16a, 18a) between the apertur~s 64 and the first row 44a o~ cooling holes 44 for providing an effective, substantially uniform boundary layer of coolant 38.
Component test~ conducted on this preferred embodiment of the invention indicate the formation of effective film cooling wi~hout the need for conventional cooling nugget structure having film cooling slots. More specifically, both the outer and inner support portions 54 and 56 are characterized by the absence of structure such as a cooling nugget lip for forming an annular plenum for receivin~ the coolant 38 from the coolant apertures 64 to for~ a boundary layer. In the prior art, a film cooling boundary layer is typically formed by cooling holes feeding an annular U-shaped plenum having an annular outlet slot to form a substantially uniform film cooling boundary layer therefro~. However, in accordance with the preferrad e~bodiment of the present invention as described above, the coolant apertures 64 disposed simply in the arcuate apex 62 8 Patent 13L~-1969 are effective for cooling the co~bustor liner upstream ends (16a, 18a) without the need for a conventional cooling nugget structure.
As shown in Figure 3, the baffles 48 are conventional and are conventionally joined to the central portion apertures 52 and spaced at least in part from the first legs 58 for forming a channel 70 therebetween.
Conventional impingement-type cooling holes 72 are conventionally formed through the first leg 58 to impinge the coolant 38 against the back side of the baffle 48 and then flow generally parallel along the sur~ace of the first leg 58 in the channel 70. The coolant ~rom khe channel 70 then flows over the apex 62 and is disposed between the coolant 38 from the apertures 64 and the combustion gases 40. It is believed that this cooperation of the coolant 38 from the channel 70 assists in providing film cooling by the coolant 38 from the apertures 64 against the liner upstrea~
ends 16a, 18a.
Since the dome plate 24 may be formed ~rom a unitary sheet metal ~ember and conventionally formed using stamping, bending, punching, and EDM operations, ~he dome plate 24 ~ay be more easily manufactured at reduced cost as co~pared to multi-piece dome plates of varying thicknes~
which require more expensive machining operations including the use of lathes, for example. Furthermore, since the dome plate 24 may be simply bolted to the outer and inner liners 16.and 18, the fabrication mPthod for the entire combustor dome 22 is simplified, which also reduces cost, and allows for relatively easy disassembly and repair and replacement of component parts thereof.
Illustrated in Figure 5 is an alternate embodiment of the present invention wherein each of the outer and inner support portions 54, 56 (inner support portion 56 being shown) may additionally include an annular ring 74 suitably conventionally fixedly connected to the concave side of the apex 62, ~or example by brazing. The coolant aper~ure 64 may then be ~ormed through both the apex 62 and through the ~d r~ J
_9_ Patent 13L~-1969 ring 74 coaxially about the longitudinal axis 68. In this way, a relatively long coolant aperture 64, i.e. longer than the thickness T of the dome plate 24, may be provided for more accurately directing the coolant 38 to impinge against 5 the liners 16, 18. The coolant apertures 64 may, therefore, have a relatively high length-to-diameter ratio as is typically found in a conventional, machined cooling nugget for more accurately directing the coolant ~8 for ensuring the formation of a substantially uniform film cooling boundary layer.
In the preferred embodiment of the invention disclosed above, the outer and inner support portions 54 and 56 including the coolant apertures 64 have been shown by tests to be effective for suitably cooling the combustor liners 16, 18 disposed adjacent to the apertures 64, and for initiating the film cooling boundary layer from the first row 44a of the inclined holes 44. In one embodiment of the inventi~n, the spacing L between the coolant apertures 64 and the first row 44a o~ inclined holes is about 0.5 inches (12.7 mm). The acute angles A for the outer and inner support portions 54, 56 are 54 and 44, respectively. The inclined holes 44 are inclined at about an angle of 20 relative to the liners 16, 18 and have a pitch-to-diameter ratio of about 6.
In alternate embodiments of the present invention, the outer and inner support portions 54 and 56 may be utilized with conventional film cooling nuggets formed in the liners 16, 18 instead of using the inclined apertures, or ~ultiholes, 44. However, it is preferred that the first row of film cooling nuggets is spaced as close as practical to the coolant apertures 64 for ensuring effective cooling of the liners at that location.
While there have been described herein what are considered to be preferred embodiments of the present invention, other modifications of the invention shall be apparent to those skilled in the art from the teachings herein, and it is, therefore, desired to be secured in the ~3~ ~ ~?~
-10- Patent 13LN-1969 appended claims all such modiflcations as fall within the true spirit and scope of the invention.
Claims (12)
1. A combustor dome comprising an annular dome plate disposed coaxially about an axial centerline axis, said dome plate including:
an annular central portion having a plurality of circumferentially spaced apertures for receiving a respective plurality of carburetors;
radially outer and inner support portions extending from said central portion for joining said dome plate to combustion liners;
each of said outer and inner support portions including a first leg extending from said central portion, a second leg, and an arcuate apex joining said first leg to said second leg, said apex having a uniform thickness and a plurality of circumferentially spaced coolant apertures for channeling cooling air therethrough,
an annular central portion having a plurality of circumferentially spaced apertures for receiving a respective plurality of carburetors;
radially outer and inner support portions extending from said central portion for joining said dome plate to combustion liners;
each of said outer and inner support portions including a first leg extending from said central portion, a second leg, and an arcuate apex joining said first leg to said second leg, said apex having a uniform thickness and a plurality of circumferentially spaced coolant apertures for channeling cooling air therethrough,
2. A combustor dome according to claim 1 wherein said second leg is straight and spaced from said first leg for joining said dome plate to one of said combustion liners, and each of said coolant apertures has a longitudinal axis disposed at an acute angle relative to said second leg for channeling said coolant therethrough in an outward direction for impinging said coolant on said one combustion liner at said acute angle.
3. A combustor dome according to claim 2 wherein said coolant apertures are predeterminedly circumferentially spaced apart for providing a substantially uniform boundary layer of said coolant for film cooling said combustion liners.
4. A combustor dome according to claim 3 wherein each of said coolant apertures has a diameter, and said coolant apertures are circumferentially spaced apart a distance about twice said diameter.
-12- Patent 13LN-1969
-12- Patent 13LN-1969
5. A combustor dome according to claim 3 wherein said outer and inner support portions are characterized by the absence of structure for forming an annular plenum for receiving said coolant from said coolant apertures to form said boundary layer.
6. A combustor dome according to claim 3 wherein said dome plate is a unitary member having a substantially constant thickness.
7. A combustor dome according to claim 6 wherein said dome plate is a sheet metal member.
8. A combustor dome according to claim 3 further including a plurality of baffles joined to said central portion apertures and spaced at least in part from said first legs of said outer and inner supports.
9. A combustor dome according to claim 3 further including a ring fixedly joined to a concave side of said apex, and said coolant aperture extends through both said ring and said apex.
10. A combustor dome according to claim 3 further including:
a radially outer combustion liner upstream end joined to said second leg of said outer support;
a radially inner combustion liner upstream end joined to said second leg of said inner support:
each of said liner upstream ends including a plurality of rows of circumferentially spaced inclined cooling holes and a first row of said inclined cooling holes is predeterminedly spaced downstream from said coolant apertures so that said coolant boundary layer from said coolant apertures initiates film cooling from said inclined cooling holes.
-13- Patent 13LN-1969
a radially outer combustion liner upstream end joined to said second leg of said outer support;
a radially inner combustion liner upstream end joined to said second leg of said inner support:
each of said liner upstream ends including a plurality of rows of circumferentially spaced inclined cooling holes and a first row of said inclined cooling holes is predeterminedly spaced downstream from said coolant apertures so that said coolant boundary layer from said coolant apertures initiates film cooling from said inclined cooling holes.
-13- Patent 13LN-1969
11. A combustor dome according to claim 10 further including a plurality of bolts fixedly joining said dome plate to said outer and inner combustion liner upstream ends.
12. The invention as defined in any of the preceding claims including any further features of novelty disclosed.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US644,139 | 1991-01-22 | ||
| US07/644,139 US5142871A (en) | 1991-01-22 | 1991-01-22 | Combustor dome plate support having uniform thickness arcuate apex with circumferentially spaced coolant apertures |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA2056474A1 true CA2056474A1 (en) | 1992-07-23 |
Family
ID=24583610
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA002056474A Abandoned CA2056474A1 (en) | 1991-01-22 | 1991-11-28 | Combustor dome |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US5142871A (en) |
| JP (1) | JPH0776622B2 (en) |
| AU (1) | AU640324B2 (en) |
| CA (1) | CA2056474A1 (en) |
| DE (1) | DE4131069C2 (en) |
| FR (1) | FR2671856B1 (en) |
| GB (1) | GB2252152B (en) |
| IL (1) | IL99421A0 (en) |
| SE (1) | SE510613C2 (en) |
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| JP2597800B2 (en) * | 1992-06-12 | 1997-04-09 | ゼネラル・エレクトリック・カンパニイ | Gas turbine engine combustor |
| US5402634A (en) * | 1993-10-22 | 1995-04-04 | United Technologies Corporation | Fuel supply system for a staged combustor |
| US5406798A (en) * | 1993-10-22 | 1995-04-18 | United Technologies Corporation | Pilot fuel cooled flow divider valve for a staged combustor |
| DE19508111A1 (en) * | 1995-03-08 | 1996-09-12 | Bmw Rolls Royce Gmbh | Heat shield arrangement for a gas turbine combustor |
| FR2751054B1 (en) * | 1996-07-11 | 1998-09-18 | Snecma | ANNULAR TYPE FUEL INJECTION ANTI-NOX COMBUSTION CHAMBER |
| DE19629191C2 (en) * | 1996-07-19 | 1998-05-14 | Siemens Ag | Process for cooling a gas turbine |
| JPH1183017A (en) * | 1997-09-08 | 1999-03-26 | Mitsubishi Heavy Ind Ltd | Combustor for gas turbine |
| US6735950B1 (en) * | 2000-03-31 | 2004-05-18 | General Electric Company | Combustor dome plate and method of making the same |
| DE10048864A1 (en) | 2000-10-02 | 2002-04-11 | Rolls Royce Deutschland | Combustion chamber head for a gas turbine |
| US6546732B1 (en) * | 2001-04-27 | 2003-04-15 | General Electric Company | Methods and apparatus for cooling gas turbine engine combustors |
| US6530227B1 (en) * | 2001-04-27 | 2003-03-11 | General Electric Co. | Methods and apparatus for cooling gas turbine engine combustors |
| FR2825779B1 (en) * | 2001-06-06 | 2003-08-29 | Snecma Moteurs | COMBUSTION CHAMBER EQUIPPED WITH A CHAMBER BOTTOM FIXING SYSTEM |
| US6568079B2 (en) | 2001-06-11 | 2003-05-27 | General Electric Company | Methods for replacing combustor liner panels |
| US6581285B2 (en) | 2001-06-11 | 2003-06-24 | General Electric Co. | Methods for replacing nuggeted combustor liner panels |
| US6546733B2 (en) * | 2001-06-28 | 2003-04-15 | General Electric Company | Methods and systems for cooling gas turbine engine combustors |
| DE10214573A1 (en) * | 2002-04-02 | 2003-10-16 | Rolls Royce Deutschland | Combustion chamber of a gas turbine with starter film cooling |
| US6725667B2 (en) * | 2002-08-22 | 2004-04-27 | General Electric Company | Combustor dome for gas turbine engine |
| US6986201B2 (en) * | 2002-12-04 | 2006-01-17 | General Electric Company | Methods for replacing combustor liners |
| US6904676B2 (en) | 2002-12-04 | 2005-06-14 | General Electric Company | Methods for replacing a portion of a combustor liner |
| US6782620B2 (en) | 2003-01-28 | 2004-08-31 | General Electric Company | Methods for replacing a portion of a combustor dome assembly |
| FR2856468B1 (en) * | 2003-06-17 | 2007-11-23 | Snecma Moteurs | TURBOMACHINE ANNULAR COMBUSTION CHAMBER |
| US7065955B2 (en) * | 2003-06-18 | 2006-06-27 | General Electric Company | Methods and apparatus for injecting cleaning fluids into combustors |
| US7310952B2 (en) * | 2003-10-17 | 2007-12-25 | General Electric Company | Methods and apparatus for attaching swirlers to gas turbine engine combustors |
| US20050122704A1 (en) * | 2003-10-29 | 2005-06-09 | Matsushita Electric Industrial Co., Ltd | Method for supporting reflector in optical scanner, optical scanner and image formation apparatus |
| US7269958B2 (en) | 2004-09-10 | 2007-09-18 | Pratt & Whitney Canada Corp. | Combustor exit duct |
| US7506512B2 (en) * | 2005-06-07 | 2009-03-24 | Honeywell International Inc. | Advanced effusion cooling schemes for combustor domes |
| US7451600B2 (en) * | 2005-07-06 | 2008-11-18 | Pratt & Whitney Canada Corp. | Gas turbine engine combustor with improved cooling |
| FR2911668B1 (en) | 2007-01-18 | 2009-03-20 | Snecma Sa | COMBUSTION CHAMBER OF A TURBOMACHINE |
| US8171736B2 (en) * | 2007-01-30 | 2012-05-08 | Pratt & Whitney Canada Corp. | Combustor with chamfered dome |
| FR2931929B1 (en) * | 2008-05-29 | 2010-06-04 | Snecma | ANNULAR COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE |
| US7926283B2 (en) * | 2009-02-26 | 2011-04-19 | General Electric Company | Gas turbine combustion system cooling arrangement |
| DE102009033592A1 (en) * | 2009-07-17 | 2011-01-20 | Rolls-Royce Deutschland Ltd & Co Kg | Gas turbine combustion chamber with starter film for cooling the combustion chamber wall |
| US8973365B2 (en) * | 2010-10-29 | 2015-03-10 | Solar Turbines Incorporated | Gas turbine combustor with mounting for Helmholtz resonators |
| US11280214B2 (en) * | 2014-10-20 | 2022-03-22 | Raytheon Technologies Corporation | Gas turbine engine component |
| US10222065B2 (en) * | 2016-02-25 | 2019-03-05 | General Electric Company | Combustor assembly for a gas turbine engine |
| US10724740B2 (en) * | 2016-11-04 | 2020-07-28 | General Electric Company | Fuel nozzle assembly with impingement purge |
| US10634353B2 (en) | 2017-01-12 | 2020-04-28 | General Electric Company | Fuel nozzle assembly with micro channel cooling |
| US11092076B2 (en) * | 2017-11-28 | 2021-08-17 | General Electric Company | Turbine engine with combustor |
| US11859819B2 (en) | 2021-10-15 | 2024-01-02 | General Electric Company | Ceramic composite combustor dome and liners |
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| GB796501A (en) * | 1955-06-09 | 1958-06-11 | Lucas Industries Ltd | Improvements relating to the construction of combustion chambers, flame tubes and the like |
| GB1108131A (en) * | 1963-12-10 | 1968-04-03 | Lucas Industries Ltd | Combustion apparatus |
| US3385055A (en) * | 1966-11-23 | 1968-05-28 | United Aircraft Corp | Combustion chamber with floating swirler rings |
| US3780529A (en) * | 1971-08-05 | 1973-12-25 | Gen Motors Corp | Combustion apparatus |
| US3736746A (en) * | 1971-08-13 | 1973-06-05 | Gen Electric | Recirculating annular slot fuel/air carbureting system for gas turbine combustors |
| BE795867A (en) * | 1972-03-01 | 1973-06-18 | Gen Electric | DEVICE FOR UNIFORMISING THE FLOW OF AIR IN A GAS TURBINE |
| GB1427146A (en) * | 1972-09-07 | 1976-03-10 | Rolls Royce | Combustion apparatus for gas turbine engines |
| US4912922A (en) * | 1972-12-19 | 1990-04-03 | General Electric Company | Combustion chamber construction |
| US3854285A (en) * | 1973-02-26 | 1974-12-17 | Gen Electric | Combustor dome assembly |
| GB1429677A (en) * | 1973-03-20 | 1976-03-24 | Rolls Royce | Gas turbine engine combustion equipment |
| FR2312654A1 (en) * | 1975-05-28 | 1976-12-24 | Snecma | COMBUSTION CHAMBERS IMPROVEMENTS FOR GAS TURBINE ENGINES |
| US3990232A (en) * | 1975-12-11 | 1976-11-09 | General Electric Company | Combustor dome assembly having improved cooling means |
| US4194358A (en) * | 1977-12-15 | 1980-03-25 | General Electric Company | Double annular combustor configuration |
| US4222230A (en) * | 1978-08-14 | 1980-09-16 | General Electric Company | Combustor dome assembly |
| US4485630A (en) * | 1982-12-08 | 1984-12-04 | General Electric Company | Combustor liner |
| US4870818A (en) * | 1986-04-18 | 1989-10-03 | United Technologies Corporation | Fuel nozzle guide structure and retainer for a gas turbine engine |
| US5117637A (en) * | 1990-08-02 | 1992-06-02 | General Electric Company | Combustor dome assembly |
-
1991
- 1991-01-22 US US07/644,139 patent/US5142871A/en not_active Expired - Fee Related
- 1991-08-06 AU AU81667/91A patent/AU640324B2/en not_active Ceased
- 1991-09-05 IL IL99421A patent/IL99421A0/en not_active IP Right Cessation
- 1991-09-11 FR FR9111228A patent/FR2671856B1/en not_active Expired - Fee Related
- 1991-09-12 JP JP3260422A patent/JPH0776622B2/en not_active Expired - Lifetime
- 1991-09-16 SE SE9102686A patent/SE510613C2/en not_active IP Right Cessation
- 1991-09-18 DE DE4131069A patent/DE4131069C2/en not_active Expired - Fee Related
- 1991-09-20 GB GB9120154A patent/GB2252152B/en not_active Expired - Fee Related
- 1991-11-28 CA CA002056474A patent/CA2056474A1/en not_active Abandoned
Also Published As
| Publication number | Publication date |
|---|---|
| DE4131069A1 (en) | 1992-07-23 |
| IL99421A0 (en) | 1992-08-18 |
| FR2671856B1 (en) | 1995-05-05 |
| GB9120154D0 (en) | 1991-11-06 |
| AU8166791A (en) | 1992-07-30 |
| JPH0776622B2 (en) | 1995-08-16 |
| GB2252152A (en) | 1992-07-29 |
| DE4131069C2 (en) | 1997-05-22 |
| SE9102686D0 (en) | 1991-09-16 |
| SE510613C2 (en) | 1999-06-07 |
| JPH04295517A (en) | 1992-10-20 |
| SE9102686L (en) | 1992-07-23 |
| FR2671856A1 (en) | 1992-07-24 |
| GB2252152B (en) | 1994-10-05 |
| AU640324B2 (en) | 1993-08-19 |
| US5142871A (en) | 1992-09-01 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| FZDE | Discontinued |