Hybrid combustor assembly and method of operation

• US 10,641,169 B2
• Filed: 06/09/2017
• Issued: 05/05/2020
• Est. Priority Date: 06/09/2017
• Status: Active Grant

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Vise, Steven Clayton, Zelina, Joseph, Johnson, Arthur Wesley, Cooper, Clayton Stuart, Pal, Sibtosh
• Primary Examiner(s): Manahan, Todd E
• Assistant Examiner(s): Nguyen, Thuyhang N
• Application Number:
  US15/618,682
• Publication Number:
  US 20180355793A1
• Time in Patent Office: 1,061 Days
• CPC Class Codes: F02C 3/16 the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
• CPC Class Codes: F02C 7/222 Fuel flow conduits, e.g. manifolds
• CPC Class Codes: F02K 7/00 Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof rocket-engine plants F02K9/00
• CPC Class Codes: F02K 7/08 the jet being continuous
• CPC Class Codes: F02K 7/10 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
• CPC Class Codes: F02K 7/20 Composite ram-jet/pulse-jet engines
• CPC Class Codes: F23R 2900/00015 Trapped vortex combustion chambers
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/58 Cyclone or vortex type combustion chambers
• CPC Class Codes: F23R 7/00 Intermittent or explosive combustion chambers

Abstract

A hybrid combustion system, and method of operation, for a propulsion system is provided. The hybrid combustion system defines a radial direction, a circumferential direction, and a longitudinal centerline in common with the propulsion system extended along a longitudinal direction. The hybrid combustion system includes a rotating detonation combustion (RDC) system comprising an annular outer wall and an annular inner wall each generally concentric to the longitudinal centerline and together defining a RDC chamber and a RDC inlet, the RDC system further comprising a nozzle located at the RDC inlet defined by a nozzle wall. The nozzle defines a lengthwise direction extended between a nozzle inlet and a nozzle outlet along the lengthwise direction, and the nozzle inlet is configured to receive a flow of oxidizer. The nozzle further defines a throat between the nozzle inlet and the nozzle outlet, and wherein the nozzle defines a converging-diverging nozzle. The hybrid combustion system further includes an inner liner extended generally along the longitudinal direction; an outer liner extended generally along the longitudinal direction and disposed outward of the inner liner along the radial direction; a bulkhead wall disposed at the upstream end of the inner and outer liners, in which the bulkhead wall extends generally in the radial direction and couples the inner liner and the outer liner, and wherein the inner liner, the outer liner, and the bulkhead wall together define a primary combustion chamber, and further wherein the RDC system and bulkhead wall together define a RDC outlet through the bulkhead wall and adjacent to the primary combustion chamber; and a fuel manifold assembly extended at least partially through the bulkhead wall, in which the fuel manifold assembly defines a fuel manifold assembly exit disposed adjacent to the primary combustion chamber.

Claims

1. A combustion system for a propulsion system, the combustion system comprising:

a rotating detonation combustion (RDC) system comprising a RDC chamber and a RDC inlet, the RDC system further comprising a nozzle configured to receive a flow of oxidizer, the nozzle configured to selectively receive a flow of fuel and provide the flow of fuel to the flow of oxidizer through the nozzle;

a bulkhead wall coupling together an inner liner and an outer liner, wherein the inner liner, the outer liner, and the bulkhead wall together define a combustion chamber, and further wherein the RDC system and bulkhead wall together define a RDC outlet through the bulkhead wall and adjacent to the combustion chamber;

a fuel manifold assembly extended at least partially through the bulkhead wall, wherein the fuel manifold assembly defines a fuel manifold assembly exit positioned adjacent to the combustion chamber; and

a deflagrative combustion system formed at least by the inner liner, the outer liner, the bulkhead wall, and the fuel manifold assembly.

2. The combustion system of claim 1, wherein the fuel manifold assembly is further in fluid communication with the nozzle of the RDC system to provide the flow of fuel to the RDC system.

3. The combustion system of claim 2, wherein the RDC system comprises a fuel injection port in fluid communication with the fuel manifold assembly, the fuel manifold assembly configured to selectively provide the flow of fuel to the fuel injection port.

4. The combustion system of claim 3, wherein the fuel injection port of the RDC system comprises a fuel outlet opening positioned between a nozzle inlet and a nozzle outlet, wherein the fuel outlet opening is configured to provide the flow of fuel from the fuel manifold assembly to the RDC chamber.

5. The combustion system of claim 4, wherein the nozzle inlet and the nozzle outlet together form a converging-diverging nozzle.

6. The combustion system of claim 2, wherein the fuel manifold assembly is configured to selectively provide the flow of fuel to the nozzle of the RDC system, and further wherein the fuel manifold assembly is configured to selectively provide a flow of fuel to the combustion chamber through the fuel manifold assembly exit.

7. The combustion system of claim 6, wherein the fuel manifold assembly is configured to provide a first flow of fuel to the combustion chamber at a first operating condition and a second flow of fuel to the nozzle of the RDC system at a second operating condition different from the first operating condition.

8. The combustion system of claim 6, wherein the fuel manifold assembly exit is formed through the bulkhead wall.

9. The combustion system of claim 1, wherein the RDC system comprises a plurality of the nozzle each positioned in adjacent arrangement along a circumferential direction.

10. The combustion system of claim 1, wherein the nozzle of the RDC system comprises a nozzle wall extended generally annularly around a longitudinal centerline.

11. The combustion system of claim 1, wherein the deflagrative combustion system comprises a trapped vortex cavity within the combustion chamber.

12. The combustion system of claim 11, wherein the deflagrative combustion system comprises a first wall at a first radius, a second wall at a second radius different from the first radius, and a transition wall therebetween coupling the first wall and the second wall, and wherein the first wall, the second wall, and the transition wall together form the trapped vortex cavity.

13. The combustion system of claim 12, wherein the first wall, the second wall, and the transition wall are formed at one or more of the inner liner, the outer liner, or the bulkhead wall of the deflagrative combustion system.

14. The combustion system of claim 11, wherein at least one of the bulkhead wall, the outer liner, and the inner liner comprises one or more oxidizer openings adjacent to the combustion chamber.

15. The combustion system of claim 14, wherein at least one of the oxidizer openings is positioned adjacent to the trapped vortex cavity.

16. The combustion system of claim 1, wherein the RDC system comprises an annular outer wall and an annular inner wall together forming the RDC chamber.

17. The combustion system of claim 1, wherein the nozzle of the RDC system comprises a nozzle inlet configured to receive the flow of oxidizer to the RDC chamber.

18. The combustion system of claim 17, wherein the nozzle of the RDC system comprises a nozzle outlet, and wherein a nozzle throat is formed between the nozzle inlet and the nozzle outlet.

19. The combustion system of claim 1, wherein the RDC system is positioned radially inward of the fuel manifold assembly.