CA2572044A1

CA2572044A1 - Combustor construction

Info

Publication number: CA2572044A1
Application number: CA 2572044
Authority: CA
Inventors: Nagaraja Rudrapatna; Oleg Morenko; Bhawan B. Patel
Original assignee: Pratt and Whitney Canada Corp
Current assignee: Pratt and Whitney Canada Corp
Priority date: 2006-12-22
Filing date: 2006-12-22
Publication date: 2008-06-22
Anticipated expiration: 2026-12-22
Also published as: CA2572044C

Abstract

A reverse flow combustor for a gas turbine engine having an outer combustor liner and an inner combustor liner defining an annular combustion chamber,and a compound-angle frustoconical portion in the outer liner having a first and second conical slopes towards an engine centreline..

Description

COMBUSTOR CONSTRUCTION
TECHNICAL FIELD

[0001] The invention relates to a gas turbine combustor, and more particularly, to the construction of such a combustor.
BACKGROUND OF THE ART

[0002] A reverse flow combustor for a gas turbine engine comprises an annular bulkhead or combustor dome in which is mounted a number of fuel nozzles. From the dome, inside and outside combustor liner walls extend to contain the combustion gases which reverse direction and exit the combustion zone via a large/outer exit duct and a small/inner exit duct towards the high and low pressure turbine zones. With all combustors, the space inside the combustor, or combustion volume, is designed to provide the desired combustion characteristics, while the space outside the combustor, between the combustor and surrounding engine case, is designed to permit the desired airflow around the combustor. However, the constraints of the engine configuration do not always permit both to be individually optimized, and consequently trade-offs are some time necessary. Nonetheless, there is a desire to improve the overall efficiency and performance of combustors, while ever reducing costs and weight.

SiJNIIMARY

[0003] In one aspect, provided is a reverse flow combustor for a gas turbine engine comprising an outer liner and an inner liner cooperating to define an annular reverse flow combustion chamber having a cylindrical head portion, the outer liner having a compound-angle frustoconical portion extending downstream from the cylindrical head portion relative to airflow inside the combustor, the compound-angle frustoconical portion including a first frustoconical portion extending from the cylindrical head portion and having a first conical slope towards an engine centreline and a second frustoconical portion extending from the first frustoconical portion and having a second conical slope towards the engine centreline, the first conical slope being greater than the second conical slope.

[0004] In another aspect, provided is a gas turbine engine comprising a case housing compressor, combustor and turbine stages in serial flow communication, the compressor stage including a centrifugal impeller with a diffuser stage having diffuser pipes, the combustor stage have a reverse flow combustion liner with an outer liner having a compound-angle frustoconical portion extending downstream from the cylindrical head portion relative to airflow inside the combustor, a first frustoconical section of the compound-angle frustoconical portion extending from the cylindrical head portion and having a first conical slope towards an engine centreline, a second frustoconical section of the compound-angle frustoconical portion extending from the first frustoconical section and having a second conical slope towards the engine centreline, the first conical slope being greater than the second conical slope.

DESCRIPTION OF THE DRAWINGS

[0005] The invention is illustrated by way of example in the accompanying drawings, in which:

[0006] Figure 1 is an axial cross-sectional view through a prior art gas turbine engine showing the various components that are assembled to produce an engine.

[0007] Figure 2 is a detailed axial cross-section through a prior art combustor.

[0008] Figure 3 is a detailed axial cross-section through a combustor in accordance with the invention.

[0009] Figure 4 is an enlarged view of a portion of Figure 3.

[00010] Further details will be apparent from the detailed description included below.

DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS

[00011] Figure 1 shows an axial cross-section through a turbofan gas turbine engine. It will be understood however that the invention is applicable to any type of gas turbine engine with an annular reverse flow combustor, such as a turboshaft engine, a turboprop engine, or auxiliary power unit. Air intake into the engine passes over fan blades 1 in a fan case 2 and is then split into an outer annular flow through the bypass duct 3 and an inner flow through the low-pressure axial compressor 4 and high-pressure centrifugal compressor 5. Compressed air exits the compressor 5 through a diffuser 6 and is contained within a plenum 7 that surrounds the combustor 8. Fuel is supplied to the combustor 8 through fuel tubes 9 which is mixed with air from the plenum 7 when sprayed through nozzles into the combustor 8 as a fuel air mixture that is ignited. A
portion of the compressed air within the plenum 7 is admitted into the combustor 8 through orifices in the side walls to create a cooling air curtain along the combustor walls or is used for cooling to eventually mix with the hot gases from the combustor and pass over the nozzle guide vane 10 and turbines 11 before exiting the tail of the engine as exhaust.

[00012] Figure 2 shows a detailed axial cross-section through a prior art combustor 8. The outer combustor liner 12 and the inner combustor liner 13 define the annular combustion chamber into which fuel-air mixture is injected and ignited. The outer combustor liner 12 is axially restrained with a plurality of support pins 14. The ends of the support pins 14 radially slidingly engage a boss 15 in the outer combustor liner 12 which permits radial expansion and contraction while restraining the combustor 8 axially to an inside wall of the bypass duct 3.

[00013] The large exit duct 16 extends from the outer liner 12 and the small exit duct 17 extends from the inner liner 13 defining a reverse flow combustor duct that directs hot gases from a forward direction to a rearward direction passing the nozzle guide vanes 10.

[00014] Figure 3 illustrates a combustor in accordance with the invention. The sheet metal combustor 8 has an outer liner 12 comprising a compound-angle frustoconical portion 20 extending the entire distance between an axially extending cylindrical head portion 22, in which the boss 15 is provided, and an entry portion 24 of the large exit duct 16. The cylindrical head portion 22 provides a desired primary combustion zone, but is located in a position more or less on the same radius as the exits of diffuser 6.
Consequently, compound-angle frustoconical portion 20 is comprised of a first frustoconical portion 20a, having a first conical slope or angle a, and a second frustoconical portion 20b, having a second conical slope angle (3, where a >(3, preferably such (3 is in the range of 0.7a and 0.3a.
Bends A, B, and C in the sheet metal of outer liner 12 define frustoconical portions 20, 20a and 20b. Bend B is located axially generally in alignment with, but preferably slightly downstream or, the diffuser outlet (relative to flow exiting the diffuser outlet). Bend B provides a hinge line between adjacent sections. The radius of bend B is preferably relatively "sharp" - i.e. with a radius of less than an inch. Bend C is provided between the LED 16 and the frustoconical portion 20. Bend A is provided between the cylindrical head section 22 and the frustoconical portion 20. A plurality of dilution holes 26 are provided in first frustoconical portion 20a, also downstream of the diffuser outlet.

[00015] A butt weld 23 (provided in the region indicated by the circle 23 in Figure 4) is preferably provided, in any suitable manner, to join adjacent sections of the second frustoconical portion 20b. Effusion cooling holes 21 are provided through the outer liner, in particular, through the compound-angle frustoconical portion 20, and more particularly though the hinge line provided at bend B, and through the butt weld 23. Preferably two rows of holes are provided through the weld region.

[00016] By providing a compound-angle frustoconical portion 20, clearance is maintained between the outer liner 12 and the fishtails of diffuser 6 as the cylindrical head 22 is joined to the LED 16, thereby optimizing airflow around combustor 8 within plenum 7 while optimizing combustion volume inside the combustor. As mentioned above, this allows flow and combustor performance to be optimized. Effusion cooling augments the design by provided cooling where required to cool local hot spots in the kinked design. The sheet metal liner provides a low-cost, easy to manufacture and lightweight solution. The butt weld between adjacent sections of the liner and LED

provide joining without unnecessary surface disruptions to obstruct airflow. Providing cooling through the weld region.

[00017] Although the above description relates to a specific preferred embodiment as presently contemplated by the inventors, it will be understood that the invention in its broad aspect includes mechanical and functional equivalents of the elements described herein.

Claims

1. A reverse flow combustor for a gas turbine engine comprising an outer liner and an inner liner cooperating to define an annular reverse flow combustion chamber having a cylindrical head portion, the outer liner having a compound-angle frustoconical portion extending downstream from the cylindrical head portion relative to airflow inside the combustor, the compound-angle frustoconical portion including a first frustoconical portion extending from the cylindrical head portion and having a first conical slope towards an engine centreline and a second frustoconical portion extending from the first frustoconical portion and having a second conical slope towards the engine centreline, the first conical slope being greater than the second conical slope.

2. A reverse flow combustor according to claim 1 wherein the first and second frustoconical portions meet at a circumferentially-extending hinge line.

3. A reverse flow combustor according to claim 2 wherein the hinge line has a bend radius of less than 1 inch.

4. A reverse flow combustor according to claim 3, wherein the hinge line includes a plurality of effusion cooling holes therethrough, the holes angled relative to a surface of the liner in which the holes are provided.

5. A reverse flow combustor according to claim 1, wherein the second frustoconical section comprises two portions of substantially identical conical slope and a butt weld interposed between and joining said two portions.

6. A reverse flow combustor according to claim 4, wherein the butt weld is adjacent the hinge line and a plurality of effusion cooling holes are provided through the butt weld.

7. A reverse flow combustor according to claim 1 wherein the first and second frustoconical portions meet angularly at a line adjacent an exit of at least one diffuser pipe of the engine.

8. A reverse flow combustor according to claim 4 wherein the conical slopes of the first and second frustoconical portions are selected to provide a desired clearance between the at least one diffuser pipe exit.

9. A reverse flow combustor according to claim 1 wherein first frustoconical portion includes a plurality of dilution holes.

10. A reverse flow combustor according to claim 1 wherein a ratio of the second conical slope to the first conical slope is in the range of 0.7 to 1 and 0.3 to 1.

11. A gas turbine engine comprising a case housing compressor, combustor and turbine stages in serial flow communication, the compressor stage including a centrifugal impeller with a diffuser stage having diffuser pipes, the combustor stage have a reverse flow combustion liner with an outer liner having a compound-angle frustoconical portion extending downstream from the cylindrical head portion relative to airflow inside the combustor, a first frustoconical section of the compound-angle frustoconical portion extending from the cylindrical head portion and having a first conical slope towards an engine centreline, a second frustoconical section of the compound-angle frustoconical portion extending from the first frustoconical section and having a second conical slope towards the engine centreline, the first conical slope being greater than the second conical slope.

12. A gas turbine engine according to claim 11 wherein the first and second frustoconical portions meet at a hinge line.

13. A gas turbine engine according to claim 11 wherein the hinge line has a bend radius of less than 1 inch.

14. A gas turbine engine according to claim 11 wherein the first and second frustoconical portions meet angularly at a line adjacent an exit of at least one diffuser pipe of the engine.

15. A gas turbine engine according to claim 14 wherein the conical slopes of the first and second frustoconical portions are selected to provide a desired clearance between the at least one diffuser pipe exit.

16. A reverse flow combustor according to claim 11 wherein first frustoconical portion includes a plurality of dilution holes.

17. A reverse flow combustor according to claim 11 wherein a ratio of the second conical slope to the first conical slope is in the range of 0.7 to 1 and 0.3 to 1.

18. A reverse flow combustor according to claim 12, wherein the hinge line location includes a plurality of effusion cooling holes therethrough, the holes angled relative to a surface of the liner in which the holes are provided.

19. A reverse flow combustor according to claim 11, wherein the second frustoconical section comprises two portions of substantially identical conical slope and a butt weld interposed between and joining said two portions.