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Flutter sensing and control system for a gas turbine engine

Inactive Publication Date: 2008-11-06
UNITED TECH CORP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0008]A method of controlling a gas turbine engine includes sensing a flutter condition and increasing a dis

Problems solved by technology

At certain aircraft operating conditions, these airfoils may be subjected to flutter, or self-induced oscillations.
During flutter, aerodynamic forces couple with each airfoil's elastic and inertial forces, which may increase the kinetic energy of each airfoil and produce negative damping.
Disadvantageously, the airfoil oscillations caused by flutter may become so severe that fracture or failure of the airfoils is possible.
Disadvantageously, all of these methods result in system compromises, small to moderate performance losses and may be expensive to incorporate into existing gas turbine engine systems.

Method used

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  • Flutter sensing and control system for a gas turbine engine
  • Flutter sensing and control system for a gas turbine engine
  • Flutter sensing and control system for a gas turbine engine

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Embodiment Construction

[0014]FIG. 1 illustrates a gas turbine engine 10 which suspends from a pylon 11 and may include (in serial flow communication) a fan section 12, a low pressure compressor 14, a high pressure compressor 16, a combustor 18, a high pressure turbine 20 and a low pressure turbine 22. During operation, air is pulled into the gas turbine engine 10 by the fan section 12, is pressurized by the compressors 14, 16, and is mixed with fuel and burned in the combustor 18. Hot combustion gases generated within the combustor 18 flow through the high and low pressure turbines 20, 22, which extract energy from the hot combustion gases.

[0015]In a two spool design, the high pressure turbine 20 utilizes the extracted energy from the hot combustion gases to power the high pressure compressor 16 through a high speed shaft 19, and a low pressure turbine 22 utilizes the energy extracted from the hot combustion gases to power the low pressure compressor 14 and the fan section 12 though a low speed shaft 21. ...

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PUM

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Abstract

A gas turbine engine system includes a nacelle, a fan casing within the nacelle, a variable area fan nozzle, a sensor and a controller. The sensor detects an airfoil flutter condition. The controller communicates with the sensor and is operable to move the variable area fan nozzle to influence a discharge airflow area in response to the detection of the airfoil flutter condition.

Description

BACKGROUND OF THE INVENTION[0001]This invention generally relates to a gas turbine engine, and more particularly to a flutter sensing system for a gas turbine engine.[0002]Gas turbine engines typically include a compressor section, a combustor section and a turbine section. Air is pressurized in the compressor section and is mixed with fuel and burned in the combustor section to add energy to expand the air and accelerate the airflow into the turbine section. The hot combustion gases that exit the combustor section flow downstream through the turbine section, which extracts kinetic energy from the expanding gases and converts the energy into shaft horsepower to drive the compressor section.[0003]In a turbofan gas turbine engine, for example, a fan section is included upstream of the compressor section. Combustion gases are discharged from the gas turbine engine through a core exhaust nozzle and fan air is discharged through an annular fan exhaust nozzle defined at least partially by...

Claims

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Application Information

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IPC IPC(8): F02C9/22
CPCF01D17/08F01D17/14F02C9/20F05D2270/10
Inventor ROSENKRANS, WILLIAM E.MORRIS, ROBERT J.
Owner UNITED TECH CORP