Convertible gas turbine propulsion system
First Claim
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.
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Accused Products
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.
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Citations
23 Claims
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1. A convertible gas turbine propulsion system operable in multiple output modes, the propulsion system comprising:
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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. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8)
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9. A gas turbine propulsion system comprising:
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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. - View Dependent Claims (10, 11, 12, 13, 14, 15, 16, 17, 18, 19)
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20. A gas turbine propulsion system comprising:
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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. - View Dependent Claims (21, 22, 23)
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Specification