Mehtod and controller for operating a gas turbine engine
First Claim
1. A method for operating a gas turbine engine installed in an aircraft, wherein the:
- gas turbine engine includes a compressor, a turbine, and a shaft connecting the turbine to the compressor, and wherein the method comprises;
running a computer dynamic model of the gas turbine engine, wherein the computer dynamic model has inputs including engine operating conditions of the gas turbine engine and aircraft operating conditions of the aircraft; and
calculating a dynamic limit on mechanical power extraction from the shaft based at least on the running of the computer dynamic model of the gas turbine engine.
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Accused Products
Abstract
A controller for operating a gas turbine engine, wherein the gas turbine engine is installable in an installation platform, wherein the gas turbine engine includes a compressor, a turbine, and a shaft connecting the turbine to the compressor. The controller includes a program which instructs the controller to run a computer dynamic model of the gas turbine engine, wherein the computer dynamic model has inputs including engine operating conditions and installation platform operating conditions. The controller also is programmed to calculate a dynamic limit on mechanical power extraction from the shaft based at least on the running of the computer dynamic model of the gas turbine engine. A method for operating a gas turbine engine installed in an aircraft includes running a computer dynamic model of the engine and calculating a dynamic limit on mechanical power extraction from a shaft of the engine based at least on the running of the model.
28 Citations
20 Claims
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1. A method for operating a gas turbine engine installed in an aircraft, wherein the:
- gas turbine engine includes a compressor, a turbine, and a shaft connecting the turbine to the compressor, and wherein the method comprises;
running a computer dynamic model of the gas turbine engine, wherein the computer dynamic model has inputs including engine operating conditions of the gas turbine engine and aircraft operating conditions of the aircraft; and
calculating a dynamic limit on mechanical power extraction from the shaft based at least on the running of the computer dynamic model of the gas turbine engine. - View Dependent Claims (2, 3, 4, 5)
- gas turbine engine includes a compressor, a turbine, and a shaft connecting the turbine to the compressor, and wherein the method comprises;
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6. A controller for operating a gas turbine engine installed in an aircraft, wherein the gas turbine engine includes a compressor, a turbine, and a shaft connecting the turbine to the compressor, and wherein the controller includes a program which instructs the controller to:
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a) run a computer dynamic model of the gas turbine engine, wherein the computer dynamic model has inputs including engine operating conditions of the gas turbine engine and aircraft operating conditions of the aircraft; and
b) calculate a dynamic limit on mechanical power extraction from the shaft based at least on the running of the computer dynamic model of the gas turbine engine. - View Dependent Claims (7, 8, 9, 10, 11, 12, 13)
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14. A controller for operating a gas turbine engine, wherein the gas turbine engine is installable in an installation platform, wherein the gas turbine engine includes a compressor, a turbine, and a shaft connecting the turbine to the compressor, and wherein the controller includes a program which instructs the controller to:
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a) run a computer dynamic model of the gas turbine engine, wherein the computer dynamic model has inputs including engine operating conditions of the gas turbine engine and installation platform operating conditions of the installation platform; and
b) calculate a dynamic limit on mechanical power extraction from the shaft based at least on the running of the computer dynamic model of the gas turbine engine. - View Dependent Claims (15, 16, 17, 18, 19, 20)
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Specification