Onboard supplemental power system at varying high altitudes
AssigneeSteward-Davis International, Inc.
InventorStanley W. Epstein
Life of this patent
Estimating the term…
Abstract
Systems and methods for supplementing a power system to achieve consistent operation at varying altitudes are disclosed herein. A hybrid power system comprising a single power source driving multiple generators may implement a power recovery turbine to drive a supercharger compressor, which may provide compressed air at increased altitudes. The supplemental power system disclosed herein provides necessary shaft horsepower at high altitudes to drive a generator and produce cooling air.
Claims20
A gas turbine power system for an aircraft, comprising:
- a gas turbine engine having a sensor system configured to measure the air mass flow through the engine, and an exhaust nozzle having a variable opening responsive to the sensor system;
- a power recovery turbine coupled to the variable opening in the gas turbine engine;
- a first compressor driven by the power recovery turbine, and configured to deliver compressed air to the gas turbine engine;
- a second compressor coupled to the gas turbine engine or the power recovery turbine;
- and
- an exhaust duct coupled between the variable opening and the power recovery turbine, wherein the sensor system comprises a first pressure sensor located adjacent to an air intake of the gas turbine engine, and a second pressure sensor located in the exhaust duct adjacent to the variable opening.
A gas turbine power system for an aircraft, comprising:
- a gas turbine engine having a sensor system configured to measure the air mass flow through the engine, and an exhaust nozzle having a variable opening responsive to the sensor system;
- a power recovery turbine coupled to the variable opening in the gas turbine engine;
- a first compressor driven by the power recovery turbine, and configured to deliver compressed air to the gas turbine engine;
- a second compressor coupled to the gas turbine engine or the power recovery turbine;
- and
- an air intercooler coupled between the first compressor and an air intake of the gas turbine engine.
A gas turbine power system for an aircraft, comprising:
- a gas turbine engine having a sensor system configured to measure the air mass flow through the engine, and an exhaust nozzle having a variable opening responsive to the sensor system;
- a power recovery turbine coupled to the variable opening in the gas turbine engine;
- a first compressor driven by the power recovery turbine, and configured to deliver compressed air to the gas turbine engine;
- a second compressor coupled to the gas turbine engine or the power recovery turbine;
- and
- a clutch coupled between, and configured to engage and disengage, the gas turbine engine and the power recovery turbine.
A method of regulating the power of a gas turbine power system installed on an aircraft, the method comprising:
- measuring the air mass flow through a gas turbine engine having an air intake and an exhaust outlet;
- adjusting, as a function of the measured air mass flow, a variable opening nozzle coupled to the exhaust outlet of the gas turbine engine to approximate sea level back pressure;
- directing exhaust from the gas turbine engine through the adjusted variable opening nozzle;
- driving a power recovery turbine with the exhaust;
- driving a first compressor with the power recovery turbine and routing compressed air generated by the first compressor to the air inlet of the gas turbine engine;
- and
- driving a second compressor with the gas turbine engine or the power recovery turbine.
A method of regulating the power of a gas turbine power system installed on an aircraft, the method comprising:
- measuring the air mass flow through a gas turbine engine having an air intake and an exhaust outlet;
- adjusting, as a function of the measured air mass flow, a variable opening nozzle coupled to the exhaust outlet of the gas turbine engine;
- directing exhaust from the gas turbine engine through the adjusted variable opening nozzle;
- driving a power recovery turbine with the exhaust;
- driving a first compressor with the power recovery turbine and routing compressed air generated by the first compressor to the air inlet of the gas turbine engine;
- and
- driving a second compressor with the gas turbine engine or the power recovery turbine;
- and
- wherein the adjustment of the variable opening nozzle is also a function of the altitude of the aircraft.
A gas turbine power system for an aircraft, comprising:
- means for measuring the air mass flow through a gas turbine engine;
- means, responsive to the means for measuring, for variably opening an exhaust nozzle coupled to the gas turbine engine;
- means, coupled to the exhaust nozzle, for driving a first compressor;
- means for delivering a first portion of compressed air from the first compressor to the gas turbine engine;
- and
- means, coupled to the gas turbine engine or the means for driving the first compressor, for further compressing a second portion of the compressed air and routing it to an air conditioning system.
Dependencies are inferred from the claim text.