Pulse detonation engines and components thereof

• US 7,526,912 B2
• Filed: 10/31/2005
• Issued: 05/05/2009
• Est. Priority Date: 10/31/2005
• Status: Expired due to Fees

• Current Assignee: General Electric Company
• Original Assignee: General Electric Company
• Inventors: Rasheed, Adam, Tangirala, Venkat Eswarlu, Dean, Anthony John, Vandervort, Christian Lee
• Primary Examiner(s): Casaregola; Louis J
• Application Number:
  US11/262,652
• Publication Number:
  US 20080006019A1
• Time in Patent Office: 1,282 Days
• Field of Search: 60/383.8, 60/393.9, 60/394, 60/397.6, 60/397.8, 602/47, 602/48
• US Class Current: 60/247
• CPC Class Codes: F23C 15/00 Apparatus in which combustion takes place in pulses influenced by acoustic resonance in a gas mass for generating combustion products of high pressure or high velocity F23R7/00; starting devices F23D11/42
• CPC Class Codes: F23R 3/005 Combined with pressure or heat exchangers
• CPC Class Codes: F23R 7/00 Intermittent or explosive combustion chambers
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A pulse detonation engine comprises a primary air inlet; a primary air plenum located in fluid communication with the primary air inlet; a secondary air inlet; a secondary air plenum located in fluid communication with the secondary air inlet, wherein the secondary air plenum is substantially isolated from the primary air plenum; a pulse detonation combustor comprising a pulse detonation chamber, wherein the pulse detonation chamber is located downstream of and in fluid communication with the primary air plenum; a coaxial liner surrounding the pulse detonation combustor defining a cooling plenum, wherein the cooling plenum is in fluid communication with the secondary air plenum; an axial turbine assembly located downstream of and in fluid communication with the pulse detonation combustor and the cooling plenum; and a housing encasing the primary air plenum, the secondary air plenum, the pulse detonation combustor, the coaxial liner, and the axial turbine assembly.

Claims

1. A pulse detonation engine comprising:

a primary air inlet;

a primary air plenum located in fluid communication with the primary air inlet;

a secondary air inlet;

a secondary air plenum located in fluid communication with the secondary air inlet, wherein the secondary air plenum is substantially isolated from the primary air plenum;

a pulse detonation combustor comprising a pulse detonation chamber, wherein the pulse detonation chamber is located downstream of and in fluid communication with the primary air plenum;

a coaxial liner surrounding the pulse detonation combustor defining a cooling plenum, wherein the cooling plenum is in fluid communication with the secondary air plenum;

an axial turbine assembly located downstream of and in fluid communication with the pulse detonation combustor and the cooling plenum; and

a housing encasing the primary air plenum, the secondary air plenum, the pulse detonation combustor, the coaxial liner, and the axial turbine assembly.

2. The pulse detonation engine of claim 1, further comprising

a transition piece located downstream of and in fluid communication with the pulse detonation combustor and the cooling plenum, and located upstream of and in fluid communication with the axial turbine assembly.

3. The pulse detonation engine of claim 2, wherein the transition piece further comprises a turbulent flow mixer.

4. The pulse detonation engine of claim 1, further comprising a compressor located upstream of the pulse detonation combustor.

5. The pulse detonation engine of claim 4, wherein the compressor is located in fluid communication with the primary air plenum.

6. The pulse detonation engine of claim 4, wherein the compressor is located in fluid communication with the primary air plenum and the secondary air plenum.

7. The pulse detonation engine of claim 4, wherein the compressor is located within the housing.

8. The pulse detonation engine of claim 1, wherein the primary air plenum is defined by an inner wall of the housing and an outer wall of an inner housing that defines the secondary air plenum.

9. The pulse detonation engine of claim 1, wherein the cooling plenum is defined by an inner wall of the coaxial liner and an outer wall of the pulse detonation combustor.

10. The pulse detonation engine of claim 1, further comprising a second pulse detonation combustor located downstream of and in fluid communication with the axial turbine assembly.

11. The pulse detonation engine of claim 1, further comprising a plurality of pulse detonation chambers.

15. The pulse detonation engine of claim 2, wherein the transition piece comprises a body configured to modify a velocity profile of a high-pressure gas exiting a pulse detonation chamber.

16. pulse detonation engine of claim 15, further comprising a turbulent flow mixer located on a surface of the body.

17. The pulse detonation engine of claim 16, wherein the turbulent flow mixer is located on an outer surface of the body.

18. The pulse detonation engine of claim 15, further comprising a plurality of turbulent flow mixers located on the surface of the body.

19. The pulse detonation engine of claim 15, wherein the body comprises a truncated funnel shape.

12. A pulse detonation engine comprising:

a housing;

a first opening in the housing defining a primary air inlet;

a primary air plenum located in fluid communication with the primary air inlet;

a second opening in the housing defining a secondary air inlet;

a secondary air plenum located in fluid communication with the secondary air inlet, wherein the secondary air plenum is defined by an inner housing and wherein the primary air plenum is defined by an inner wall of the housing and an outer wall of the inner housing such that the secondary air plenum is substantially isolated from the primary air plenum;

a pulse detonation combustor comprising a plurality of pulse detonation chambers, wherein the pulse detonation chambers are each located downstream of and in fluid communication with the primary air plenum;

a coaxial liner surrounding the pulse detonation combustor;

a cooling plenum defined by an inner wall of the coaxial liner and an outer wall of the pulse detonation combustor, wherein the cooling plenum is in fluid communication with the secondary air plenum;

an axial turbine assembly located downstream of and in fluid communication with the pulse detonation combustor and the cooling plenum; and

wherein the housing encases the primary air plenum, the secondary air plenum, the pulse detonation combustor, the coaxial liner, and the axial turbine assembly.

13. The pulse detonation engine of claim 12, further comprising

a transition piece located downstream of and in fluid communication with The pulse detonation combustor and the cooling plenum and located upstream of and in fluid communication with the axial turbine assembly.

14. The pulse detonation engine of claim 13, wherein the transition piece further comprises a turbulent flow mixer.