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Speed modification system for gas turbine engine to allow trimming of excess thrust

A speed correction, gas turbine technology, used in gas turbine power plants, turbine/propulsion fuel delivery systems, gas turbine installations, etc.

Inactive Publication Date: 2004-06-23
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The target fan speed state is determined based on environmental conditions, engine operating characteristics, and desired thrust rating, due to hydrodynamic fuel system limitations; arrangements to individually adjust the target fan speed on an engine on an engine-by-engine basis also not done

Method used

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  • Speed modification system for gas turbine engine to allow trimming of excess thrust
  • Speed modification system for gas turbine engine to allow trimming of excess thrust
  • Speed modification system for gas turbine engine to allow trimming of excess thrust

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Embodiment Construction

[0019] Detailed Description of Preferred Embodiments

[0020] Performance characteristic data for a particular type of engine can be determined by testing a gas turbine sample of an engine type after prototype construction. These performance characteristic data are used to generate fan speed correction characteristics which represent actual engine thrust output levels relative to nominal speed in a given engine model. These resulting fan speed correction characteristics indicate the corresponding change in fan speed required in order to match the actually generated thrust with the desired nominal thrust. figure 1 Is a graphical representation of typical fan speed performance characteristics for each member of an engine model versus nominal speed setting, indicating the level of fan speed correction required to produce the desired level of thrust at each specific speed setting. The fan speed performance characteristics 100-110 are empirically determined by evaluating a large n...

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PUM

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Abstract

The present invention provides a fan speed indication system enabling the operator to control engine rotational speed to match specific thrust performance to flight requirements. The invention accommodates variations in engine thrust performance measured at manufacture or overhaul. In one embodiment, the invention provides an analog speed signal to flight control apparatus. The invention may also be configured to provide a digital speed signal to engine power management control apparatus.

Description

field of invention [0001] This invention relates to a thrust control system for a gas turbine engine, and more particularly to a system for providing a speed signal to the operator based on the measured thrust operating characteristics of a particular gas turbine engine and the engine type The difference between the standard thrust operating characteristics to compensate for changes in thrust performance, so that the pilot can more accurately match the thrust output of the engine to the thrust requirement. Background technique [0002] Design, manufacture and control variations and accumulated tolerances of gas turbine engines result in variations in operating performance between different engines within the same engine model. One of these operational properties is thrust output. To provide for safe operation of aircraft, gas turbine engines are generally designed such that any given engine is guaranteed to produce a predetermined minimum guaranteed or rated thrust level re...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D27/10F02C9/00F02C9/28
CPCF02C9/28F05D2270/053F05D2270/304
Inventor D·M·卡马斯T·J·罗森菲尔德B·G·欣格斯
Owner GENERAL ELECTRIC CO