Convertible gas turbine propulsion system

• US 8,511,058 B2
• Filed: 11/29/2007
• Issued: 08/20/2013
• Est. Priority Date: 11/29/2007
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Agrawal, Rajendra K., Sirica, Steven J., Schneider, William F.
• Primary Examiner(s): Rodriguez, William H
• Assistant Examiner(s): KIM, CRAIG SANG
• Application Number:
  US11/998,291
• Publication Number:
  US 20090139202A1
• Time in Patent Office: 2,091 Days
• Field of Search: 60/391.7, 60/391.5, 60/391.63, 607/91, 244/7.R, 244/7.A, 244/17.11, 244/17.13, 244/17.19, 244/17.21, 244/23.B, 244/23.D, 244/17.23, 244/17.25, 244/53.R, 244/55, 244/58, 244/60, 244/12.3
• US Class Current: 60/39.15
• CPC Class Codes: F02C 6/206 the vehicles being airscrew driven
• CPC Class Codes: F02C 7/36 Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user F02C3/107 - F02C3/13 and F02C7/32 take precedence; couplings for transmitting rotation F16D; gearing in general F16H

Abstract

A convertible gas turbine propulsion system operates in multiple output modes. The convertible gas turbine propulsion system comprises a gas generator, a first power turbine, a secondary propulsion system and an exhaust duct. The gas generator is configured to produce exhaust gas. The first power turbine is aligned with the gas generator to receive the exhaust gas. The secondary propulsion system is in series with the gas generator and the first power turbine. The exhaust duct coaxially extends from the first power turbine to the secondary propulsion system. The exhaust duct includes an exhaust port for opening the exhaust duct to ambient air pressure and permitting exhaust gas to bypass the secondary propulsion system. In various embodiments of the invention, the first power turbine is connected to a first rotary propulsion system, and the secondary propulsion system comprises a second power turbine or a nozzle.

Claims

1. A convertible gas turbine propulsion system operable in multiple output modes, the propulsion system comprising:

a gas generator for producing exhaust gas;

a gas generator turbine driven by the exhaust gas;

a first power turbine aligned in series with the gas generator turbine to receive the exhaust gas;

a primary propulsion system coupled to the first power turbine and configured to produce thrust in a first axial direction;

a secondary propulsion system in series with the gas generator turbine and the first power turbine, such that the propulsion system is configured to direct airflow in series through the gas generator turbine, the first power turbine and the secondary propulsion system, wherein the secondary propulsion system is configured to produce thrust in a second axial direction transverse to the first axial direction;

an exhaust duct coaxially extending from the first power turbine to the secondary propulsion system to direct exhaust gas into the secondary propulsion system;

an exhaust port positioned within the exhaust duct between the first power turbine and the secondary propulsion system; and

a retractable annular cowling for selectively opening the exhaust port to ambient air pressure axially between the first power turbine and the secondary propulsion system to permit exhaust gas to bypass the secondary propulsion system, the entire retractable annular cowling being axially displaceable from a first position axially spanning the exhaust port to a second position axially adjacent the exhaust duct.

2. The propulsion system of claim 1 wherein the first power turbine and the gas generator turbine are configured as a turboshaft engine.

3. The propulsion system of claim 1 wherein the exhaust port effectively ceases powered output of the secondary propulsion system by the exhaust gas when the retractable annular cowling is in an open position by producing a negligible pressure differential across the secondary propulsion system.

4. The propulsion system of claim 1 wherein the exhaust gas effectively powers the secondary propulsion system when the retractable annular cowling is in a closed position by producing an operable pressure differential across the secondary propulsion system.

5. The propulsion system of claim 1 wherein the secondary propulsion system is coupled to a second power turbine mechanically uncoupled from the first power turbine such that the first power turbine and the second power turbine rotate independently and such that the propulsion system is configured to direct the exhaust gas in series through the gas generator turbine, the first power turbine and the second power turbine.

6. The propulsion system of claim 5 and further comprising:

a first shaft connected to the first power turbine for driving a first rotary output system comprising the primary propulsion system; and

a second shaft connected to the second power turbine for driving a second rotary output system comprising the secondary propulsion system.

7. The propulsion system of claim 6 wherein:

the first rotary output system comprises a rotary propulsion system connected to the first shaft for providing vertical and horizontal thrust; and

the second rotary output system comprises a propeller propulsion system connected to the second shaft for producing horizontal thrust.

8. The propulsion system of claim 1 wherein:

the first power turbine is connected to a rotary propulsion system comprising the primary propulsion system; and

the secondary propulsion system comprises a nozzle for accelerating the exhaust gas.

9. A gas turbine propulsion system comprising:

a primary propulsion system comprising;

a combustor for producing exhaust gas;

a gas generator turbine powered by the exhaust gas;

a first power turbine powered by the exhaust gas;

a first propulsor connected to the first power turbine and configured to produce thrust in a first axial direction;

a compressor connected to the gas generator turbine; and

an annular first exhaust duct extending from the first power turbine;

a secondary propulsion system including;

an annular second exhaust duct positioned an axial distance aft of the first power turbine radially within a downstream end of the first exhaust duct to define a bypass passage radially outward of the annular second exhaust duct and radially inward of the downstream end of the first exhaust duct; and

a retractable annular cowling comprising a ring radially disposed between the first exhaust duct and the second exhaust duct axially aft to the axial distance in an open position, wherein the cowling is axially displaceable to span the axial distance and close the bypass passage turbine in a closed position for selectively closing off flow of the exhaust gas to the bypass passage; and

a second propulsor configured to receive the exhaust gas and produce thrust in a second axial direction transverse to the first axial direction.

10. The gas turbine propulsion system of claim 9 wherein:

the first annular exhaust duct is radially larger at a second end than at a first end such that the first annular exhaust duct surrounds the second annular exhaust duct; and

the retractable cowling is positioned within the second annular exhaust duct.

11. The gas turbine propulsion system of claim 10 wherein the second propulsor includes a second power turbine that is disposed within the second exhaust duct downstream of the first power turbine such that the propulsion system is configured to direct the exhaust gas in series through the gas generator turbine, the first power turbine and the second power turbine.

12. The gas turbine propulsion system of claim 11 wherein the second power turbine is mechanically uncoupled from the first power turbine.

13. The gas turbine propulsion system of claim 11 wherein the annular cowling controls a pressure differential across the second power turbine.

14. The gas turbine propulsion system of claim 11 wherein the annular cowling produces a greater pressure differential across the second power turbine when in the closed position as compared to a pressure differential across the second power turbine when in an open position.

15. The gas turbine propulsion system of claim 11 wherein the annular cowling opens the bypass passage to ambient pressure when in the open position.

16. The gas turbine propulsion system of claim 11 wherein:

the first propulsor is connected to the second power turbine.

17. The gas turbine propulsion system of claim 16 wherein the first propulsor comprises horizontal rotors and the second propulsor comprises vertical rotors.

18. The gas turbine propulsion system of claim 11 wherein the second power turbine includes variable vanes and a variable vane actuation mechanism to regulate pressure differential across the second power turbine.

19. The gas turbine propulsion system of claim 10 wherein the second annular exhaust duct comprises an exhaust nozzle such that the second propulsor comprises a flow accelerating duct.

20. A gas turbine propulsion system comprising:

a gas generator combustor for producing exhaust gas;

a gas generator turbine for receiving exhaust gas from the combustor;

a first power turbine disposed downstream from the gas generator turbine;

a first rotary propulsion system connected to the first power turbine and including a first output shaft extending in a first axial direction;

a first exhaust duct positioned aft of the first power turbine to define a pressure chamber, wherein the first power turbine is driven by a pressure differential between the gas generator turbine and the pressure chamber;

a second power turbine downstream of the first power turbine within the first exhaust duct such that the propulsion system is configured to direct the exhaust gas in series through the gas generator turbine, the first power turbine, the pressure chamber and the second power turbine,

a second exhaust duct extending into the pressure chamber within the first exhaust duct, wherein the second exhaust duct includes an axially retractable annular cowling comprising a ring that is selectively positioned to control a pressure differential across the second power turbine; and

a second rotary propulsion system connected to the second power turbine and including a second output shaft extending in a second axial direction transverse to the first axial direction.

21. The gas turbine propulsion system of claim 20 wherein the axially retractable annular cowling of the second exhaust duct is positioned in an open configuration to produce a negligible pressure differential across the second power turbine.

22. The gas turbine propulsion system of claim 20 wherein the negligible pressure differential across the second power turbine permits the second power turbine to windmill.

23. The gas turbine propulsion system of claim 20 wherein the axially retractable annular cowling of the second exhaust duct is positioned in a closed configuration to produce a pressure differential across the second power turbine proportional to the pressure in the pressure chamber and ambient pressure aft of the second power turbine.