Inert gas turbine engine

• US 5,373,698 A
• Filed: 07/02/1992
• Issued: 12/20/1994
• Est. Priority Date: 07/02/1992
• Status: Expired due to Term

• Current Assignee: Alan Taylor
• Original Assignee: Alan Taylor
• Inventors: Taylor, Alan
• Primary Examiner(s): Husar, Stephen F.
• Application Number:
  US07/907,723
• Time in Patent Office: 901 Days
• Field of Search: 60/669, 60/650, 60/682, 60/651, 60/671, 60/39.182, 60/269, 60/726
• US Class Current: 60/669
• CPC Class Codes: F01K 23/08 with working fluid of one cycle heating the fluid in another cycle
• CPC Class Codes: F02C 1/10 Closed cycles
• CPC Class Codes: F02K 7/08 the jet being continuous

Abstract

An inert gas turbine engine contains a working fluid closed loop system leading from an expansion turbine which is in fluid flow relationship with an expansion chamber. Working fluid within the expansion chamber is heated by the combustion of compressed air and fuel within the combustion chamber. The heated working fluid within the expansion chamber rotates an expansion turbine which in turn rotates the compressor. Combusted gases do not contact the turbine blades. The rotation of the expansion turbine is controlled by the temperature and pressure of the working fluid within the expansion chamber. The temperature of the expansion turbine and working fluid within the expansion chamber may be controlled by the use of various cooling means. Additional turbines may be incorporated within the engine to be turned by the working fluid within the expansion chamber. Heated working fluid which rotates the turbines may be cooled and compressed within the closed loop system prior to re-entry into the expansion chamber and reheating therein.

Claims

1. A thrust producing inert gas turbine engine comprising:

an inlet section having a compressor therein;

a combustion section in air flow relationship with the inlet section and compressor, said combustion section comprising a combustion chamber in air flow relationship with the compressor;

an expansion chamber in heat transfer relationship with the combustion chamber;

an exhaust section in air flow relationship with the combustion section;

an expansion turbine in fluid flow relationship with the expansion chamber wherein heated working fluid from the expansion chamber rotates the expansion turbine;

a first working fluid closed loop system comprising a condenser portion in fluid flow relationship with the expansion chamber and expansion turbine, wherein a working fluid within the expansion chamber is heated within the expansion chamber, rotates the expansion turbine and is cooled in the condenser portion prior to being reheated in the expansion chamber;

means for driving the compressor as the expansion turbine rotates, wherein air from the compressor is forced into the combustion chamber for mixture with a fuel and combustion, and wherein combustion of fuel and air within the combustion chamber heats working fluid in the expansion chamber causing the working fluid to rotate the expansion turbine and drive the compressor thereby forcing air into the combustion chamber to be mixed with fuel, combusted and exhausted through the exhaust section to produce thrust.

2. The inert gas turbine engine of claim 1 wherein the combustion chamber is annular in shape and surrounds at least a portion of the expansion chamber.

3. The inert gas turbine engine of claim 2 wherein the means for driving the compressor comprises a shaft connected to the compressor and expansion turbine.

4. The inert gas turbine engine of claim 3 wherein the closed loop system comprises a heat exchanger for cooling the working fluid.

5. The inert gas turbine engine of claim 3 wherein the closed loop system further comprises a compressor for compressing working fluid which has been heated into a gas phase within the expansion chamber.

6. The inert gas turbine engine of claim 5 wherein the closed loop system comprises a first storage tank.

7. The inert gas turbine engine of claim 6 further comprising an impulse reaction turbine in fluid flow relationship with the expansion chamber wherein the working fluid heated within the expansion chamber turns the impulse reaction turbine.

8. The inert gas turbine engine of claim 7 further comprising a variable turbine nozzle assembly located between the expansion chamber and the impulse reaction turbine and the expansion turbine for varying the flow of working fluid into said impulse reaction turbine and expansion turbine.

9. The inert gas turbine engine of claim 8 further comprising an expansion chamber thermocontrol housing having a cooling chamber therein, said cooling chamber being in heat transfer relationship with the expansion chamber for cooling and in fluid flow relationship with the compressor for allowing compressed air therein to cool the expansion chamber.

10. The inert gas turbine engine of claim 9 further comprising one or more fins located within the expansion chamber, and said fins extending into the combustion chamber.

11. The inert gas turbine engine of claim 10 wherein the fins also pass through the expansion chamber thermocontrol housing and cooling chamber.

12. The inert gas turbine engine of claim 11 further comprising a second closed loop working fluid system in parallel with the first closed loop working fluid system said second system being in fluid flow relationship with the expansion chamber and expansion turbine for cooling the working fluid from the expansion chamber and expansion turbine prior to reheating in the expansion chamber.

13. The inert gas turbine engine of claim 11 wherein the first or second closed loop system is connected to a fire extinguishing system wherein the working fluid is released from the closed loop system and used to extinguish fire within the engine or engine housing.

14. The inert gas turbine engine of claim 11 further comprising means for controlling the flow of working fluid through the first closed loop system.

15. The inert gas turbine engine of claim 14 wherein the means for controlling the flow of working fluid through the first closed loop system comprises one or more valves.

16. The inert gas turbine engine of claim 15 wherein the valves are controlled by a microprocessor to provide the correct amount of working fluid flow through the first closed loop system.

17. The inert gas turbine engine of claim 3 further comprising means for allowing working fluid within the closed loop system to cool the expansion turbine.

18. The inert gas turbine engine of claim 17 wherein the means for allowing working fluid within the closed loop system to cool the expansion turbine comprises a conduit leading from the closed loop system, said conduit being in fluid flow relationship with the expansion turbine to cool the expansion turbine.

19. The inert gas turbine engine of claim 3 further comprising a variable area reducer located within the expansion chamber for varying the volume within the expansion chamber.

20. A thrust producing inert gas turbine engine comprising:

an inlet section having a compressor therein;

a combustion section being in air flow relationship with the compressor, said combustion section including an expansion chamber in heat transfer relationship with a combustion chamber;

an expansion turbine in fluid flow relationship with the expansion chamber wherein heated working fluid from the expansion chamber rotates the expansion turbine;

an exhaust section in air flow relationship with the combustion section wherein combusted air and fuel within the combustion chamber is exhausted through said exhaust section without contacting the expansion turbine to produce thrust.