GB2491580A - A method of manufacturing a sheet metal annular combustion chamber - Google Patents
A method of manufacturing a sheet metal annular combustion chamber Download PDFInfo
- Publication number
- GB2491580A GB2491580A GB201109382A GB201109382A GB2491580A GB 2491580 A GB2491580 A GB 2491580A GB 201109382 A GB201109382 A GB 201109382A GB 201109382 A GB201109382 A GB 201109382A GB 2491580 A GB2491580 A GB 2491580A
- Authority
- GB
- United Kingdom
- Prior art keywords
- sheet metal
- width
- metal blank
- sub
- intersection
- 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.)
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- 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
- F23R3/002—Wall structures
-
- 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
-
- 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
Abstract
A method of forming a plurality of sheet metal blanks 100, each sheet metal blank has at least a first portion 102, a second portion 104 and a third portion 106. The second portion has a first width (W1 Fig 3) at a first intersection (FI1 Fig 3) with the first portion, and a second width (W2 Fig 3) at an intersection (FI2 Fig 3) with the third portion; the second width is less than the first width. Each blank has a fuel injector aperture 108 formed in the second portion, a plurality of cooling apertures 110 formed in the first portion, and a plurality of cooling apertures 112 formed in the third portion. Each blank is folded at the first intersection and at the second intersection, and each folded blank is joined to two other blanks to form an annular combustion chamber (42 Fig 7). Each blank may also include several stud or bolt apertures 116, 120, 124, and at least one dilution aperture, 118, 122. The blanks may be stamped or laser cut from a larger piece of sheet metal, and the combustion chamber may be utilized in a gas turbine engine.
Description
A METHOD OF MANUFACTURING AN ANNULAR COMBUSTION CHAMBER
The present invention relates to a method of manufacturing an annular combustion chamber and in particular to a method of manufacturing an annular gas turbine engine combustion chamber.
Conventionally an annular combustion chamber is manufactured by welding an inner annular wall to an upstream end wall and welding an outer annular wall to the upstream end wall. The upstream end wall is conventionally formed by casting and machining.
The inner and outer annular walls are conventionally formed by machining ring rolled forgings. Tiles are secured to the inner and outer walls and heat shields are secured to the upstream end wall.
The conventional method of manufacturing an annular combustion chamber is expensive and has long lead times. The conventional method of manufacturing an annular combustion chamber requires many different manufacturing techniques, e.g. casting, forging, rolling, machining and welding etc. Accordingly the present invention provides a method of manufacturing an annular combustion chamber, the method comprising the steps of:- (a) forming a plurality of sheet metal blanks, each sheet metal blank having at least a first portion, a second portion and a third portion, the second portion having a first width at a first intersection with the first portion, the second portion having a second width at a second intersection with the third portion, the second width being less than the first width, (b) forming a fuel injector aperture in the second portion of each sheet metal blank, (c) forming a plurality of cooling apertures in the first portion of each sheet metal blank, (d) forming a plurality of cooling apertures in the third portion of each sheet metal blank, (e) folding each sheet metal blank at the first intersection and folding each sheet metal blank at the second intersection, and (f) joining each sheet metal blank to two other sheet metal blanks such that the first portion of each sheet metal blank is joined to the first portion of two other sheet metal blanks, the second portion of each sheet metal blank is joined to the second portion of two other sheet metal blanks and the third portion of each sheet metal blank is joined to the third portion of two other sheet metal blanks to form an annular combustion chamber.
Step (b) may comprise forming a plurality of cooling apertures in the second portion of each sheet metal blank. Step (b) may comprise forming a plurality of stud, or bolt, apertures in the second portion of each sheet metal blank.
Step (c) may comprise forming at least one dilution aperture in the first portion of each sheet metal blank. Step (c) may comprise forming a plurality of stud, or bolt, apertures in the first portion of each sheet metal blank.
Step (d) may comprise forming at least one dilution aperture in the third portion of each sheet metal blank. Step (d) may comprise forming a plurality of stud, or bolt, apertures in the third portion of each sheet metal blank.
Step (a) may comprise laser cutting or stamping. Step (b) may comprise laser cutting.
Step (c) may comprise laser cutting. Step (d) may comprise laser cutting.
Step (f) may comprise laser welding, electron beam welding, TIC welding, brazing or bolting.
The method may comprise a step (g) of securing at least one tile to the first portion of each sheet metal blank, securing at least one tile to the third portion of each sheet metal blank and securing at least one heat shield to the second portion of each sheet metal blank.
The third portion of each sheet metal blank may have a first sub portion and a second sub portion, the first sub portion has a second width at the intersection with the second portion and the first sub portion has a third width at the intersection with the second sub portion, the third with is less than the second width, the second sub section has a fourth width at an end remote from the first sub section.
The fourth width may be greater than the third width. The fourth width may be greater than the second width.
The first portion of each sheet metal blank may have a first sub portion and a second sub portion, the first sub portion has a first width at the intersection with the second portion and the first sub portion has a fifth width at the intersection with the second sub portion, the fifth with is greater than the first width, the second sub section has a sixth width at an end remote from the first sub section.
The sixth width may be less than the fifth width. The sixth width may be less than the first width.
The present invention will be more fully described by way of example with reference to the accompanying drawings, in which:-Figure 1 is a partially cut away view of a turbofan gas turbine engine showing an annular combustion chamber made using a method according to the present invention.
Figure 2 is a longitudinal cross-sectional view through the combustion chamber shown in figure 1.
Figure 3 is a plan view of a sheet metal blank after step (a) of the method according to the present invention.
Figure 4 is a plan view of a sheet metal blank after step (d) of the method according to the present invention.
Figure 5 is a perspective view of a sheet metal blank after step (e) of the method according to the present invention.
Figure 6 is a perspective view of a number of sheet metal blanks during step (f) of the method according to the present invention.
Figure 7 is an end view of annular combustion chamber after step (f) of the method according to the present invention.
Figure 8 is a cross-sectional view through the annular combustion chamber in figure 7.
Figure 9 is a plan view of an alternative sheet metal blank after step (a) of the method according to the present invention.
Figure 10 is a cross-sectional view through an annular combustion chamber using sheet metal blanks in figure 9.
Figure 11 is a plan view of another sheet metal blank after step (a) of the method according to the present invention.
Figure 12 is a cross-sectional view through an annular combustion chamber using sheet metal blanks in figure 11.
A turbofan gas turbine engine 10, as shown in figure 1, comprises in flow series an inlet 12, a fan section 14, a compressor section 16, a combustion section 18, a turbine section 20 and an exhaust 22. The fan section 14 comprises a fan 24. The compressor section 16 comprises in flow series an intermediate pressure compressor 26 and a high pressure compressor 28. The turbine section 20 comprises in flow series a high pressure turbine 30, an intermediate pressure turbine 32 and a low pressure turbine 34. The fan 24 is driven by the low pressure turbine 34 via a shaft 40. The intermediate pressure compressor 26 is driven by the intermediate pressure turbine 32 via a shaft 38 and the high pressure compressor 28 is driven by the high pressure turbine 30 via a shaft 36. The turbofan gas turbine engine 10 operates quite conventionally and its operation will not be discussed further. The turbofan gas turbine engine 10 has a rotational axis X. The combustion section 18 comprises an annular combustion chamber 42, which is shown more clearly in figure 2. The annular combustion chamber 42 has an inner annular wall 44, an outer annular wall 46 and an upstream end wall 48 connecting the upstream ends of the inner annular wall 44 and the outer annular wall 46. The annular combustion chamber 42 is surrounded by a casing 50. The upstream end wall 48 has a plurality of circumferentially spaced fuel injector apertures 52 and each fuel injector aperture 52 has a respective one of a plurality of fuel injectors 54. The upstream end wall 48 also has a plurality of smaller diameter cooling apertures 56 through which a flow of coolant is arranged to flow in operation. The inner annular wall 44 has a plurality of circumferentially spaced dilution apertures 58 through which a flow of dilution air is arranged to flow into the annular combustion chamber 42 in operation.
The inner annular wall 44 also has a plurality of smaller diameter cooling apertures 60 through which a flow of coolant is arranged to flow in operation. The outer annular wall 46 has a plurality of circumferentially spaced dilution apertures 62 through which a flow of dilution air is arranged to flow into the annular combustion chamber 42 in operation.
The outer annular wall 46 also has a plurality of smaller diameter cooling apertures 64 through which a flow of coolant is arranged to flow in operation.
The upstream end wall 48 has a plurality of heat shields 68 secured thereto to protect a downstream surface 48B of the upstream end wall 48 from the hot gases in the annular combustion chamber 42. The heat shields 68 are circumferentially arranged and are positioned in end to end relationship. The upstream end wall 48 also has a plurality of stud apertures 57 and each heat shield 68 has a plurality of threaded studs 70 which are arranged to extend through corresponding stud apertures 57 in the upstream end wall 48 and nuts 72 are threaded onto the threaded studs 70 to secure the heat shields 68 to the upstream end wall 48. The cooling apertures 56 in the upstream end wall 48 are arranged to direct the coolant such that it impinges upon the upstream surface 68A of the heat shields 68 to cool the heat shields 68 and the heat shields 68 have effusion apertures 74 to allow the coolant to flow there-through and to form a film of coolant on the downstream surface 68B of the heat shields 68.
The inner annular wall 44 has a plurality of tiles 76 secured thereto to protect a radially outer surface 44B of the inner annular wall 44 from the hot gases in the annular combustion chamber 42. The tiles 76 are axially and circumferentially arranged and are positioned in end to end relationship. The inner annular wall 44 also has a plurality of stud apertures 59 and each tile 76 has a plurality of threaded studs 78 which are arranged to extend through corresponding stud apertures 59 in the inner annular wall 44 and nuts 80 are threaded onto the threaded studs 78 to secure the tiles 76 to the inner annular wall 44. The cooling apertures 60 in the inner annular wall 44 are arranged to direct the coolant such that it impinges upon the radially inner surface 76A of the tiles 76 to cool the tiles 76 and the tiles 76 have effusion apertures 81 to allow the coolant to flow there-through and to form a film of coolant on the radially outer surface 76B of the tiles 76.
The outer annular wall 46 has a plurality of tiles 82 secured thereto to protect a radially inner surface 46B of the outer annular wall 46 from the hot gases in the annular combustion chamber 42. The tiles 82 are axially and circumferentially arranged and are positioned in end to end relationship. The outer annular wall 46 also has a plurality of stud apertures 63 and each tile 82 has a plurality of threaded studs 84 which are arranged to extend through corresponding stud apertures 63 in the outer annular wall 46 and nuts 86 are threaded onto the threaded studs 84 to secure the tiles 82 to the outer annular wall 46. The cooling apertures 64 in the outer annular wall 46 are arranged to direct the coolant such that it impinges upon the radially outer surface 82A of the tiles 82 to cool the tiles 82 and the tiles 82 have effusion apertures 88 to allow the coolant to flow there-through and to form a film of coolant on the radially inner surface 82B of the tiles 82.
A method of manufacturing an annular combustion chamber 42 according to the present invention is shown in figures 3 to 8. The method comprises a first step (a) of forming a plurality of sheet metal blanks 100 and each sheet metal blank 100 has at least a first portion 102, a second portion 104 and a third portion 106. The second portion 104 has a first width WI at a first intersection Fli with the first portion 102, the second portion 104 has a second width W2 at a second intersection F12 with the third portion 106 and the second width W2 is less than the first width WI. A second step (b) comprises forming a fuel injector aperture 108 in the second portion 104 of each sheet metal blank 100. A third step (c) comprises forming a plurality of cooling apertures 110 in the first portion 102 of each sheet metal blank 100. A fourth step (d)comprises forming a plurality of cooling apertures 112 in the third portion 106 of each sheet metal blank 100. A fifth step (e) comprises folding each sheet metal blank 100 at the first intersection Fli and folding each sheet metal blank at the second intersection F12 and a sixth step (f) comprises joining each sheet metal blank 100 to two other sheet metal blanks 100 such that the first portion 102 of each sheet metal blank 100 is joined to the first portion 102 of two other sheet metal blanks 100, the second portion 104 of each sheet metal blank 100 is joined to the second portion 104 of two other sheet metal blanks 100 and the third portion 106 of each sheet metal blank 100 is joined to the third portion 106 of two other sheet metal blanks 100 to form an annular combustion chamber 42. Each sheet metal blank 100 has a first longitudinally extending edge 105 and a second longitudinally extending edge 107 and the first and second longitudinally extending edges 105 and 107 extend continuously along the length of the first portion 102, the second portion 104 and the third portion 106.
Step (a) may comprise laser cutting or stamping the sheet metal blanks 100 from a larger piece or sheet metal. Step (b) may comprise forming the fuel injector aperture 108 in the second portion 104 of each sheet metal blank 100 by laser cutting, but other suitable methods may be used for example stamping, electro-chemical machining or electro-discharge machining. Step (c) may comprise forming a plurality of cooling apertures 110 in the first portion 102 of each sheet metal blank 100 by laser cutting, laser drilling, electro-chemical machining or electro-discharge machining. Step (d) may comprise forming a plurality of cooling apertures 112 in the third portion 106 of each sheet metal blank 100 by laser cutting, laser drilling, electro-chemical machining or electro-discharge machining. Step (e) may comprise folding each sheet metal blank at the first intersection Fli and folding each sheet metal blank 100 at the second intersection F12 by bending the sheet metal blank 100 at the first intersection Fli and by bending the sheet metal blank 100 at the second intersection F12 using a press brake or other suitable apparatus. Step (f) may comprise joining each sheet metal blank 100 to two other sheet metal blanks 100 by laser welding, electron beam welding, TIG welding, brazing or bolting. In step (f) each longitudinally extending edge 105 and 107 respectively of each sheet metal blank 100 may be welded to a corresponding longitudinally extending edge 107 and 105 respectively of an adjacent sheet metal blank 100.
Step (b) may comprise forming a plurality of cooling apertures 114 in the second portion 104 of each sheet metal blank 100 by laser cutting, but other suitable methods may be used for example electro-chemical machining or electro-discharge machining. Step (b) may comprise forming a plurality of stud, or bolt, apertures 116 in the second portion 104 of each sheet metal blank 100 by laser cutting, but other suitable methods may be used for example electro-chemical machining or electro-discharge machining. Step (c) may comprise forming at least one dilution aperture 118 in the first portion 102 of each sheet metal blank 100 by laser cutting, but other suitable methods may be used for example stamping, electro-chemical machining or electro-discharge machining. Step (c) may comprise forming a plurality of stud, or bolt, apertures 120 in the first portion 102 of each sheet metal blank 100 by laser cutting, but other suitable methods may be used for example electro-chemical machining or electro-discharge machining. Step (d) may comprise forming at least one dilution aperture 122 in the third portion 106 of each sheet metal blank 100 by laser cutting, but other suitable methods may be used for example stamping, electro-chemical machining or electro-discharge machining. Step (d) may comprise forming a plurality of stud, or bolt, apertures 124 in the third portion 106 of each sheet metal blank 100 by laser cutting, but other suitable methods may be used for example electro-chemical machining or electro-discharge machining.
The method may comprise a step (g) of securing at least one tile 82 to the first portion 102 of each sheet metal blank 100, securing at least one tile 76 to the third portion 106 of each sheet metal blank 100 and securing at least one heat shield 68 to the second portion 104 of each sheet metal blank 100. The tiles 82 and 76 are secured to the first and third portions 102 and 106 of each sheet metal blank 100 respectively by aligning the studs 84 and 78 on the tiles 82 and 76 respectively with the stud apertures 120 and 124 in the first and third portions 102 and 106 of the sheet metal blank 100 respectively and by securing nuts 86 and 80 on the studs 84 and 78. A heat shield 68 is secured to the second portion 104 of each sheet metal blank 100 respectively by aligning the studs on the heat shield 68 with the stud apertures 57 in the second portion 104 of the sheet metal blank 100 respectively and by securing nuts 72 on the studs 70.
It is to be noted from figure 8 that the sheet metal blanks 100 have been folded, or bent, through an angle of approximately 90° at the first and second intersections Fli and F12.
In a further method of manufacturing an annular combustion chamber according to the present invention the third portion 106 of each sheet metal blank 1 OOA has a first sub portion 106A and a second sub portion 106B as shown in figure 9. The first sub portion 1 06A has a second width W2 at the second intersection Fl2 with the second portion 104 and the first sub portion 106A has a third width W3 at the intersection F13 with the second sub portion 106B, the third with W3 is less than the second width W2, the second sub section 1 06B has a fourth width W4 at an end remote from the first sub section 1 06A. The fourth width W4 may be greater than the third width W3 and/or the fourth width W4 may be greater than the second width W2. The sheet metal blanks 1 00A are also folded at the intersection F13. It is to be noted from figure 10 that the sheet metal blanks 100 have been folded, or bent, through an angle of approximately 900 at the first intersection Fli and that the sheet metal blanks 100 have been bent through angles smaller than 90° at the second intersection F12 and at the intersection F13.
In another method of manufacturing an annular combustion chamber according to the present invention the first portion 102 of each sheet metal blank I OOA has a first sub portion 102A and a second sub portion 102B as shown in figure 10. The first sub portion 102A has a first width WI at the intersection FIl with the second portion 104 and the first sub portion 1 02A has a fifth width W5 at the intersection F14 with the second sub portion 102B, the fifth with W5 is greater than the first width Wl, the second sub section 1 02B has a sixth width W6 at an end remote from the first sub section 1 02A. The sixth width W6 may be less than the fifth width W5 and/or the sixth width W6 may be less than the first width Wl. The sheet metal blanks 100B are also folded at the intersection F14. It is to be noted from figure 12 that the sheet metal blanks 100 have been folded, or bent, through an angle of approximately 90° at the second intersection F12 and that the sheet metal blanks 100 have been bent through angles smaller than 90° at the first intersection Fli and at the intersection F14.
It may be possible in another method of manufacturing an annular combustion chamber according to the present invention to form each sheet metal blank to have a first portion which has a first sub portion and a second sub portion as described with reference to figure II and a second portion which has a first sub portion and a second sub portion as described with reference to figure 9. -11 -
It may be possible in another method of manufacturing an annular combustion chamber according to the present invention to dispense with the tiles and to form each sheet metal blank to have a first portion which has a plurality of sub portions and a second portion which has a plurality of sub portions and after folding the first and second portions of each sheet metal portion the alternate sub portions of the first portion and the second portion extend generally axially and generally radially. Cooling apertures are formed in the sub portions of the first and second portions which will extend generally radially after folding the first and second portions of each sheet metal portion.
In this way the annular combustion chamber is similar to a conventional annular chamber which has Z-type cooling rings.
It is to be noted from figure 7 that the annular combustion chamber 42 is in fact polygonal in cross section and the inner annular wall and the outer annular wall is polygonal. The annular combustion chamber 42 in figure 7 has sixteen sides and thus the annular combustion chamber 42 comprises sixteen sheet metal blanks 100. The number of sides in the polygon is dependent upon the number of sheet metal blanks used to make the annular combustion chamber 42 and any suitable number of sheet metal blanks 100 may be used.
The sheet metal blanks may consist of any suitable metal or suitable alloy, for example nickel base alloys, nickel base superalloys, cobalt base alloys or cobalt base superalloys.
The advantage of the present invention is that it reduces the cost of producing an annular combustion chamber and reduces the number and types of manufacturing techniques required to manufacture the annular combustion chamber. It is estimated that there is a 95% reduction in the cost of manufacturing an annular combustion chamber.
The features of an annular combustion chamber which are costly to produce and measure in three dimensions by the conventional method are produced in two dimensions in a method according to the present invention and then folded into shape, for example in the conventional method cooling holes, dilution holes, stud holes are machined through the curved inner and outer annular walls of the annular combustion chamber whereas in the present invention the cooling holes, dilution holes, stud holes are machined through a flat sheet metal blank. Sheet metal is relatively cheap compared to ring rolled forgings. The manufacturing process used in the present invention is much cheaper and much quicker compared to the conventional method.
Claims (20)
- CLAIMS1. A method of manufacturing an annular combustion chamber, the method comprising the steps of:- (a) forming a plurality of sheet metal blanks, each sheet metal blank having at least a first portion, a second portion and a third portion, the second portion having a first width at a first intersection with the first portion, the second portion having a second width at a second intersection with the third portion, the second width being less than the first width, (b) forming a fuel injector aperture in the second portion of each sheet metal blank, (c) forming a plurality of cooling apertures in the first portion of each sheet metal blank, (d) forming a plurality of cooling apertures in the third portion of each sheet metal blank, (e) folding each sheet metal blank at the first intersection and folding each sheet metal blank at the second intersection, and (f)joining each sheet metal blank to two other sheet metal blanks such that the first portion of each sheet metal blank is joined to the first portion of two other sheet metal blanks, the second portion of each sheet metal blank is joined to the second portion of two other sheet metal blanks and the third portion of each sheet metal blank is joined to the third portion of two other sheet metal blanks to form an annular combustion chamber.
- 2. A method as claimed in claim 1 wherein step (b) comprises forming a plurality of cooling apertures in the second portion of each sheet metal blank.
- 3. A method as claimed in claim 1 or claim 2 wherein step (b) comprises forming a plurality of stud, or bolt, apertures in the second portion of each sheet metal blank.
- 4. A method as claimed in claim 1, claim 2 or claim 3 wherein step (c) comprises forming at least one dilution aperture in the first portion of each sheet metal blank.-14 -
- 5. A method as claimed in any of claims I to 4 wherein step (c) comprises forming a plurality of stud, or bolt, apertures in the first portion of each sheet metal blank.
- 6. A method as claimed in any of claims I to 5 wherein step (d) comprises forming at least one dilution aperture in the third portion of each sheet metal blank.
- 7. A method as claimed in any of claims 1 to 6 wherein step (d) comprises forming a plurality of stud, or bolt, apertures in the third portion of each sheet metal blank.
- 8. A method as claimed in any of claims 1 to 7 wherein step (a) comprises laser cutting or stamping.
- 9. A method as claimed in any of claims 1 to 8 wherein step (b) comprises laser cutting.
- 10. A method as claimed in any of clams 1 to 9 wherein step (c) comprises laser cutting.
- 11. A method as claimed in any of claims 1 to 10 wherein step (d) comprises laser cutting.
- 12. A method as claimed in any of claims 1 to 11 wherein step (f) comprises laser welding, electron beam welding, TIG welding, brazing or bolting.
- 13. A method as claimed in any of claims 1 to 12 comprising a step (g) of securing at least one tile to the first portion of each sheet metal blank, securing at least one tile to the third portion of each sheet metal blank and securing at least one heat shield to the second portion of each sheet metal blank.
- 14. A method as claimed in any of claims Ito 13 wherein the third portion of each sheet metal blank has a first sub portion and a second sub portion, the first sub portion has a second width at the intersection with the second portion and the first sub portion has a third width at the intersection with the second sub portion, the third with is less than the second width, the second sub section has a fourth width at an end remote from the first sub section.
- 15. A method as claimed in claim 14 wherein the fourth width is greater than the third width.
- 16. A method as claimed in claim 14 or claim 15 wherein the fourth width is greater than the second width.
- 17. A method as claimed in any of claims 1 to 16 wherein the first portion of each sheet metal blank has a first sub portion and a second sub portion, the first sub portion has a first width at the intersection with the second portion and the first sub portion has a fifth width at the intersection with the second sub portion, the fifth with is greater than the first width, the second sub section has a sixth width at an end remote from the first sub section.
- 18. A method as claimed in claim 17 wherein the sixth width is less than the fifth width.
- 19. A method as claimed in claim 17 or claim 18 wherein the sixth width is less than the first width.
- 20. A method of manufacturing an annular combustion chamber substantially as hereinbefore described with reference to the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB201109382A GB2491580A (en) | 2011-06-06 | 2011-06-06 | A method of manufacturing a sheet metal annular combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB201109382A GB2491580A (en) | 2011-06-06 | 2011-06-06 | A method of manufacturing a sheet metal annular combustion chamber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB201109382D0 GB201109382D0 (en) | 2011-07-20 |
| GB2491580A true GB2491580A (en) | 2012-12-12 |
Family
ID=44343405
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB201109382A Withdrawn GB2491580A (en) | 2011-06-06 | 2011-06-06 | A method of manufacturing a sheet metal annular combustion chamber |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2491580A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10502421B2 (en) | 2015-02-04 | 2019-12-10 | Rolls-Royce Plc | Combustion chamber and a combustion chamber segment |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6434821B1 (en) * | 1999-12-06 | 2002-08-20 | General Electric Company | Method of making a combustion chamber liner |
| US20090077976A1 (en) * | 2007-09-21 | 2009-03-26 | Snecma | Annular combustion chamber for a gas turbine engine |
-
2011
- 2011-06-06 GB GB201109382A patent/GB2491580A/en not_active Withdrawn
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6434821B1 (en) * | 1999-12-06 | 2002-08-20 | General Electric Company | Method of making a combustion chamber liner |
| US20090077976A1 (en) * | 2007-09-21 | 2009-03-26 | Snecma | Annular combustion chamber for a gas turbine engine |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10502421B2 (en) | 2015-02-04 | 2019-12-10 | Rolls-Royce Plc | Combustion chamber and a combustion chamber segment |
Also Published As
| Publication number | Publication date |
|---|---|
| GB201109382D0 (en) | 2011-07-20 |
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| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |