US3184918A - Cooling arrangement for crossover tubes - Google Patents

Cooling arrangement for crossover tubes Download PDF

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Publication number
US3184918A
US3184918A US288823A US28882363A US3184918A US 3184918 A US3184918 A US 3184918A US 288823 A US288823 A US 288823A US 28882363 A US28882363 A US 28882363A US 3184918 A US3184918 A US 3184918A
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tube
flametube
wall
lateral tube
lateral
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US288823A
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Robert L Mulcahey
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Raytheon Technologies Corp
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United Aircraft Corp
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Priority to US288823A priority Critical patent/US3184918A/en
Priority to GB22672/64A priority patent/GB1037955A/en
Priority to CH744364A priority patent/CH411465A/en
Priority to BE648950D priority patent/BE648950A/xx
Priority to SE7043/64A priority patent/SE302221B/xx
Priority to FR977683A priority patent/FR1398352A/en
Priority to NL6406585A priority patent/NL6406585A/xx
Application granted granted Critical
Publication of US3184918A publication Critical patent/US3184918A/en
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    • 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
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • F23R3/48—Flame tube interconnectors, e.g. cross-over tubes

Definitions

  • This invention relates to an arrangement by which to provide for cooling of the crossover tubes in a combustion chamber construction to prevent burnout of the crossover tubes and the flametube wall adjacent thereto.
  • the gas from the compressor passes either through a pluarity of separate combustion chambers or through a single annular combustion chamber within which are located a plurality of flametu'bes.
  • crossover tubes provided between adjacent fiametubes to equalize the pressures within the tubes and also to provide for ignition of the combustible mixture in adjacent flametubes after ignition has been initiated in one of them.
  • the crossover tubes interfere with the flow of air over the surface of the flametube and as a result the crossover tube or the flametube adjacent thereto frequently is overheated with resultant breakdown of the tube wall.
  • One feature of the present invention is an arrangement by which to eliminate this destructive overheating.
  • FIG. 1 is a transverse sectional view through a semiannular combustion chamber showing the flametubes in elevation.
  • FIG. 2 is a view substantially along the line 22 of FIG. 1.
  • FIG. 3 is a view substantially along the line 3-3 of FIG. 2.
  • FIG. 4 is a sectional view substantially along the line 4-4 of FIG. 2.
  • FIG. 5 is a sectional view substantially along the line 5-5 of FIG. 2.
  • the invention is shown in connection with a semiannular combustion chamber for use in gas turbine powerplants of the type shown, for example, in the Savin Patent 2,747,367.
  • Air from the compressor passes through an annular combustion chamber defined by an outer Wall 2 and a concentric inner wall 4.
  • annular duct Within this annular duct are located a plurality of substantially cylindrical flametubes 6 having at their upstream ends an end cap 8 with a plurality of openings 10 therein to receive fuel nozzles, not shown, for the injection of combustible fluid into the flametube.
  • the end cap may also have a central opening 12 for the admission of air into a central tube Within the flametube although this is not a feature of or involved in the present invention.
  • Adjacent flametubes 6 are interconnected by crossover connectors 14 extending between adjacent fiametubes.
  • Each crossover connector consists of a crossover tube 16 projecting from and suitably attached as by brazing or welding to the flametube, as best shown in FIG. 4.
  • the flametube 6 normally consists of a plurality of annular rings 20, 22 and 24 which are overlapping and welded together as best shown in FIG. 3. Each ring has a plurality of openings 26 therein for the admission of air into the flametube for cooling purposes.
  • the crossover tube element 16 is positioned in the sleeve 22 and in a position to interrupt the row of holes 26 in this sleeve.
  • the tube 16 for the upstream half of its periphery is blended into and welded into the sleeve 20 and sleeve 22.
  • the flow of air being in the direction of the arrow 28, FIG.
  • the sleeve 22 carries a downwardly projecting flange 30 positioned inside of the sleeve 22 and spaced therefrom to direct flow of cooling air between the sleeve 22 and the flange 30.
  • the sleeve 22 is spaced from the wall of the tube 16 over the area where the flange 30 is located to provide a passage 32 for the flow of cooling air into the flametube at this point.
  • the downstream side of the tube 16 has a semiannular shield 34 mounted thereon.
  • the shield 34 is suitably welded or brazed to the sleeve 22 at its inner end and at its outer end carries an inwardly projecting flange 36 engaged with and suitably secured to the tube 16.
  • the diametral edges of the shield are spaced from the tube 16 and, in this way, the shield 34 defines an opening 38 on opposite sides of the tube 16 which faces in an upstream direction and which receives cooling air to guide it around the downstream side of the tube 16 and thence through the opening 32 to flow between the fiange 3i and the adjacent wall of the sleeve 22.
  • a flametube for a combustion chamber said tube having an annular Wall with openings therein for the flow of air into the tube, said tube having a partially closed upstream end, a laterally extending crossover tube mounted in a side opening in the annular wall and projecting outwardly therefrom with the inner end of the lateral tube substantially in alignment with the annular wall, said lateral tube being welded to the flametube over substantially the upstream half of the lateral tube and having an outwardly projecting flange on the downstream half thereof located within and extending parallel to the adjacent flametube wall, the lateral tubev being spaced from the edge of the opening in the flametube Wall over substantially the downstream half of the lateral tube to form a passage for air between the lateral tube and the flametube Wall and a substantially semicylindrical shield extending around and located in spaced concentric relation to the lateral tube in the downstream side thereof, said shield being secured along its outer edge to the crossover tube at a point spaced from the flametube wall and being secured at its inner edge to the edge of the opening in the
  • a plurality of flame tubes each having a substantially cylindrical wall and arranged in substantially parallel relation to each other for a flow of air around the flametube in substantially parallel relation to the longitudinal axes of the tubes, said tubes having upstream and downstream ends, a crossover tube projecting laterally from each'flametube with the crossover tubes 7 of adjacent flametubes positioned in alignment andinterconnected and a semicylindr'ical shield positioned around and in spaced concentric relation to the crossover tube and located on the downstream side of the crossovertube, said shield extending outwardly from the flametube and being attached at its innerend, said shield being attached to the crossover tube at its outer end in spaced, relation to the flametube wall, said shield between its ends, at'its diametral edges being spaced from the crossover tube on opposite ends thereof to form openings for the em trance of cooling air into the shield, the flametube being 20 spaced from the crossover tube at the downstream side 1 of the crossover tube to provide a passage for a flow of cooling air entering the shield into the interior of
  • a combustion chamber as in claim 2 in which the crossover tube has a flange thereon on the end adjacent the flametube, said flange projecting in a downstream direction and being positioned within and in spaced relation to the Wall of the flametube for directing air entering the passage to flow along the inner wall of the flametube at the downstream side of the crossover tube.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

May 25, 1965 R. L. MULCAHEY COOLING ARRANGEMENT FOR CROSSOVER TUBES Filed June 18, 1963 United States Patent 3,184,913 COOLING ARRANGEMEEIQT FOR CROSSOVER TUB Robert L. Mulcahey, East Hartford, Conn, assignor to United Aircraft Corporation, East Hartford, Conn., a corporation of Delaware Fiied June 18, 1963, Ser. No. 288,823 3 Claims. (Cl. 60-39.66)
This invention relates to an arrangement by which to provide for cooling of the crossover tubes in a combustion chamber construction to prevent burnout of the crossover tubes and the flametube wall adjacent thereto.
In combustion chamber constructions for gas turbine engines the gas from the compressor passes either through a pluarity of separate combustion chambers or through a single annular combustion chamber within which are located a plurality of flametu'bes. In either of these constructions there are crossover tubes provided between adjacent fiametubes to equalize the pressures within the tubes and also to provide for ignition of the combustible mixture in adjacent flametubes after ignition has been initiated in one of them. The crossover tubes interfere with the flow of air over the surface of the flametube and as a result the crossover tube or the flametube adjacent thereto frequently is overheated with resultant breakdown of the tube wall. One feature of the present invention is an arrangement by which to eliminate this destructive overheating.
One arrangement by which to control the wall temperature adjacent the crossover tube is shown in the patent to Ward 2,979,898. This arrangement has been satisfactory in certain installations. However, under certain conditions it has been found that even more effective wall cooling is necessary and, accordingly, one of the principal features of the present invention is a modification or revision of the cooling arrangement of the Ward patent which more etfectively reduces the flametube wall temperature.
Other features and advantages will be apparent from the specification and claims, and from the accompanying drawing which illustrates an embodiment of the invention.
FIG. 1 is a transverse sectional view through a semiannular combustion chamber showing the flametubes in elevation.
FIG. 2 is a view substantially along the line 22 of FIG. 1.
FIG. 3 is a view substantially along the line 3-3 of FIG. 2.
'FIG. 4 is a sectional view substantially along the line 4-4 of FIG. 2.
FIG. 5 is a sectional view substantially along the line 5-5 of FIG. 2.
The invention is shown in connection with a semiannular combustion chamber for use in gas turbine powerplants of the type shown, for example, in the Savin Patent 2,747,367. Air from the compressor passes through an annular combustion chamber defined by an outer Wall 2 and a concentric inner wall 4. Within this annular duct are located a plurality of substantially cylindrical flametubes 6 having at their upstream ends an end cap 8 with a plurality of openings 10 therein to receive fuel nozzles, not shown, for the injection of combustible fluid into the flametube. The end cap may also have a central opening 12 for the admission of air into a central tube Within the flametube although this is not a feature of or involved in the present invention.
Adjacent flametubes 6 are interconnected by crossover connectors 14 extending between adjacent fiametubes. Each crossover connector consists of a crossover tube 16 projecting from and suitably attached as by brazing or welding to the flametube, as best shown in FIG. 4. Op-
3,184,918 Patented May 25, 1965 posed crossover tube elements 16 from adjacent tubes are in alignment as shown in FIG. 1 and a connector sleeve 18 establishes the remainder of the crossover connector 14.
Referring now to FIGS. 2 to 5, inclusive, the flametube 6 normally consists of a plurality of annular rings 20, 22 and 24 which are overlapping and welded together as best shown in FIG. 3. Each ring has a plurality of openings 26 therein for the admission of air into the flametube for cooling purposes. The crossover tube element 16 is positioned in the sleeve 22 and in a position to interrupt the row of holes 26 in this sleeve. The tube 16 for the upstream half of its periphery is blended into and welded into the sleeve 20 and sleeve 22. At the downstream side of the tube 16, the flow of air being in the direction of the arrow 28, FIG. 4, it carries a downwardly projecting flange 30 positioned inside of the sleeve 22 and spaced therefrom to direct flow of cooling air between the sleeve 22 and the flange 30. The sleeve 22 is spaced from the wall of the tube 16 over the area where the flange 30 is located to provide a passage 32 for the flow of cooling air into the flametube at this point.
To assist in directing the cooling air around the tube 16 and through the opening 32 the downstream side of the tube 16 has a semiannular shield 34 mounted thereon. The shield 34 is suitably welded or brazed to the sleeve 22 at its inner end and at its outer end carries an inwardly projecting flange 36 engaged with and suitably secured to the tube 16. The diametral edges of the shield are spaced from the tube 16 and, in this way, the shield 34 defines an opening 38 on opposite sides of the tube 16 which faces in an upstream direction and which receives cooling air to guide it around the downstream side of the tube 16 and thence through the opening 32 to flow between the fiange 3i and the adjacent wall of the sleeve 22.
Prior to the application of this device to the crossover tube the downstream side of the tube 16 and the wall of the sleeve 22 adjacent thereto would frequently be extensively heated to result in destructive damage to the tube and sleeve. With the arrangement shown it has been found possible to operate the gas turbine powerplant in which this invention is incorporated at maximum power over long periods of time Without damage by overheating.
It is to be understood that the invention is not limited to the specific embodiment herein illustrated and described, but may be used in other ways without departure from its spirit as defined by the following claims.
I claim:
1. A flametube for a combustion chamber, said tube having an annular Wall with openings therein for the flow of air into the tube, said tube having a partially closed upstream end, a laterally extending crossover tube mounted in a side opening in the annular wall and projecting outwardly therefrom with the inner end of the lateral tube substantially in alignment with the annular wall, said lateral tube being welded to the flametube over substantially the upstream half of the lateral tube and having an outwardly projecting flange on the downstream half thereof located within and extending parallel to the adjacent flametube wall, the lateral tubev being spaced from the edge of the opening in the flametube Wall over substantially the downstream half of the lateral tube to form a passage for air between the lateral tube and the flametube Wall and a substantially semicylindrical shield extending around and located in spaced concentric relation to the lateral tube in the downstream side thereof, said shield being secured along its outer edge to the crossover tube at a point spaced from the flametube wall and being secured at its inner edge to the edge of the opening in the flametube within which the lateral tube is positioned for directing air entering the space between the shield and 3, the lateral tube into the passage between the lateral tube and the flametube- Wall.
2. In a combustion chamber a plurality of flame tubes each having a substantially cylindrical wall and arranged in substantially parallel relation to each other for a flow of air around the flametube in substantially parallel relation to the longitudinal axes of the tubes, said tubes having upstream and downstream ends, a crossover tube projecting laterally from each'flametube with the crossover tubes 7 of adjacent flametubes positioned in alignment andinterconnected and a semicylindr'ical shield positioned around and in spaced concentric relation to the crossover tube and located on the downstream side of the crossovertube, said shield extending outwardly from the flametube and being attached at its innerend, said shield being attached to the crossover tube at its outer end in spaced, relation to the flametube wall, said shield between its ends, at'its diametral edges being spaced from the crossover tube on opposite ends thereof to form openings for the em trance of cooling air into the shield, the flametube being 20 spaced from the crossover tube at the downstream side 1 of the crossover tube to provide a passage for a flow of cooling air entering the shield into the interior of the flametube.
3. A combustion chamber as in claim 2 in which the crossover tube has a flange thereon on the end adjacent the flametube, said flange projecting in a downstream direction and being positioned within and in spaced relation to the Wall of the flametube for directing air entering the passage to flow along the inner wall of the flametube at the downstream side of the crossover tube.
References Cited by the Examiner UNITED STATES PATENTS 2,699,648 1/55 Berkey ,6039.65 2,851,859 '9/58 Foure 6039.65
2,979,898 4/61 Ward 60 '39.37 X

Claims (1)

1. A FLAMETUBE FOR A COMBUSTION CHAMBER, SAID TUBE HAVING AN ANNULAR WALL WITH OPENINGS THEREIN FOR THE FLOW OF AIR INTO THE TUBE, SAID TUBE HAVING A PARTIALLY CLOSED UPSTREAM END, A LATERALLY EXTENDING CORSSOVER TUBE MOUNTED IN A SIDE OPENING IN THE ANNULAR WALL AND PROJECTING OUTWARDLY THEREFROM WITH THE INNER END OF THE LATERAL TUBE SUBSTANTIALLY IN ALIGNMENT WITH THE ANNULAR WALL, SAID LATERAL TUBE BEING WELDED TO THE FLAMETUBE OVER SUBSTANTIALLY THE UPSTREAM HALF OF THE LATERAL TUBE AND HAVING AN OUTWARDLY PROJECTING FLANGE ON THE DOWNSTREAM HALF THEREOF LOCATED WITHIN SAID EXTENDING PARALLEL TO THE ADJACENT FLAMETUBE WALL, THE LATERAL TUBE BEING SPACED FROM THE EDGE OF THE OPENING IN THE FLAMETUBE WALL OVER SUBSTANTIALLY THE DOWNSTREAM HALF OF THE LATERAL TUBE TO FORM A PASSAGE FOR AIR BETWEEN THE LATERAL TUBE AND THE FLAMETUBE WALL AND A SUBSTANTIALLY SEMICYLINDRICAL SHIELD EXTENDING AROUND AND LOCATED IN SPACED CONCENTRIC RELATION TO THE LATERAL TUBE IN THE DOWNSTREAM SIDE THEREOF, SAID SHIELD BEING SECURED ALONG ITS OUTER EDGE TO THE CROSSOVER TUBE AT A POINT AT ITS INNER EDGE TO THE EDGE OF THE OPENING IN THE CURED AT ITS INNER EDGE TO THE EDGE OF THE OPENING IN THE FLAMETUBE WITHIN WHICH THE LATERAL TUBE IS POSITIONED FOR DIRECTING AIR ENTERING THE SPACE BETWEEN THE SHIELD AND THE LATTERAL TUBE INTO THE PASSAGE BETWEEN THE LATERAL TUBE AND THE FLAMETUBE WALL.
US288823A 1963-06-18 1963-06-18 Cooling arrangement for crossover tubes Expired - Lifetime US3184918A (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
US288823A US3184918A (en) 1963-06-18 1963-06-18 Cooling arrangement for crossover tubes
GB22672/64A GB1037955A (en) 1963-06-18 1964-06-02 Cooling arrangement for crossover tubes, linking flame tubes in a combustion chamber
CH744364A CH411465A (en) 1963-06-18 1964-06-08 Combustion chamber comprising flame tubes interconnected by junction tubes
BE648950D BE648950A (en) 1963-06-18 1964-06-08
SE7043/64A SE302221B (en) 1963-06-18 1964-06-10
FR977683A FR1398352A (en) 1963-06-18 1964-06-10 Cooling device for connecting tubes in a combustion chamber
NL6406585A NL6406585A (en) 1963-06-18 1964-06-10

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US288823A US3184918A (en) 1963-06-18 1963-06-18 Cooling arrangement for crossover tubes

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CH (1) CH411465A (en)
FR (1) FR1398352A (en)
GB (1) GB1037955A (en)
NL (1) NL6406585A (en)
SE (1) SE302221B (en)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3391535A (en) * 1966-08-31 1968-07-09 United Aircraft Corp Burner assemblies
US3439498A (en) * 1966-12-16 1969-04-22 Rolls Royce Gas turbine engine combustion chamber
US3440818A (en) * 1966-07-08 1969-04-29 Nationale D Etude De Construct Combustion and cooling air control in turbojet engines
US3811274A (en) * 1972-08-30 1974-05-21 United Aircraft Corp Crossover tube construction
US3995422A (en) * 1975-05-21 1976-12-07 General Electric Company Combustor liner structure
US4887432A (en) * 1988-10-07 1989-12-19 Westinghouse Electric Corp. Gas turbine combustion chamber with air scoops
US5402635A (en) * 1993-09-09 1995-04-04 Westinghouse Electric Corporation Gas turbine combustor with cooling cross-flame tube connector
US5438821A (en) * 1993-03-22 1995-08-08 Abb Management Ag Method and appliance for influencing the wake of combustion chamber inserts
US20130333389A1 (en) * 2012-06-15 2013-12-19 General Electric Company Cross fire tube retention system for a gas turbine engine
US20160025346A1 (en) * 2014-07-24 2016-01-28 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor
US20170292707A1 (en) * 2014-09-25 2017-10-12 Mitsubishi Hitachi Power Systems, Ltd. Combustor and gas turbine
US10161635B2 (en) 2014-06-13 2018-12-25 Rolls-Royce Corporation Combustor with spring-loaded crossover tubes
CN114174723A (en) * 2019-05-13 2022-03-11 赛峰航空器发动机 Combustion chamber comprising a device for cooling the annular housing region downstream of the chimney
US11359814B2 (en) 2015-08-28 2022-06-14 Rolls-Royce High Temperature Composites Inc. CMC cross-over tube

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2699648A (en) * 1950-10-03 1955-01-18 Gen Electric Combustor sectional liner structure with annular inlet nozzles
US2851859A (en) * 1952-07-16 1958-09-16 Onera (Off Nat Aerospatiale) Improvements in combustion chambers for turbo-jet, turbo-prop and similar engines
US2979893A (en) * 1958-04-02 1961-04-18 United Aircraft Corp Thrust reverser

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2699648A (en) * 1950-10-03 1955-01-18 Gen Electric Combustor sectional liner structure with annular inlet nozzles
US2851859A (en) * 1952-07-16 1958-09-16 Onera (Off Nat Aerospatiale) Improvements in combustion chambers for turbo-jet, turbo-prop and similar engines
US2979893A (en) * 1958-04-02 1961-04-18 United Aircraft Corp Thrust reverser

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3440818A (en) * 1966-07-08 1969-04-29 Nationale D Etude De Construct Combustion and cooling air control in turbojet engines
US3391535A (en) * 1966-08-31 1968-07-09 United Aircraft Corp Burner assemblies
US3439498A (en) * 1966-12-16 1969-04-22 Rolls Royce Gas turbine engine combustion chamber
US3811274A (en) * 1972-08-30 1974-05-21 United Aircraft Corp Crossover tube construction
US3995422A (en) * 1975-05-21 1976-12-07 General Electric Company Combustor liner structure
US4887432A (en) * 1988-10-07 1989-12-19 Westinghouse Electric Corp. Gas turbine combustion chamber with air scoops
US5438821A (en) * 1993-03-22 1995-08-08 Abb Management Ag Method and appliance for influencing the wake of combustion chamber inserts
US5402635A (en) * 1993-09-09 1995-04-04 Westinghouse Electric Corporation Gas turbine combustor with cooling cross-flame tube connector
US20130333389A1 (en) * 2012-06-15 2013-12-19 General Electric Company Cross fire tube retention system for a gas turbine engine
US10161635B2 (en) 2014-06-13 2018-12-25 Rolls-Royce Corporation Combustor with spring-loaded crossover tubes
US20160025346A1 (en) * 2014-07-24 2016-01-28 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor
US10401031B2 (en) * 2014-07-24 2019-09-03 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor
US20170292707A1 (en) * 2014-09-25 2017-10-12 Mitsubishi Hitachi Power Systems, Ltd. Combustor and gas turbine
US10584879B2 (en) * 2014-09-25 2020-03-10 Mitsubishi Hitachi Power Systems, Ltd. Combustor including a flow guide introduction portion connected to a flow guide main body portion, and a gas turbine
US11359814B2 (en) 2015-08-28 2022-06-14 Rolls-Royce High Temperature Composites Inc. CMC cross-over tube
CN114174723A (en) * 2019-05-13 2022-03-11 赛峰航空器发动机 Combustion chamber comprising a device for cooling the annular housing region downstream of the chimney
US11846420B2 (en) 2019-05-13 2023-12-19 Safran Aircraft Engines Combustion chamber comprising means for cooling an annular casing zone downstream of a chimney
CN114174723B (en) * 2019-05-13 2024-02-20 赛峰航空器发动机 Combustion chamber comprising a device for cooling an annular housing area downstream of a chimney

Also Published As

Publication number Publication date
GB1037955A (en) 1966-08-03
NL6406585A (en) 1964-12-21
CH411465A (en) 1966-04-15
SE302221B (en) 1968-07-08
FR1398352A (en) 1965-05-07
BE648950A (en) 1964-10-01

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