Transient turbine overtemperature control

Power plants – Combustion products used as motive fluid

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60 39281, F02C 928

Patent

active

057325464

ABSTRACT:
A gas turbine engine includes a compressor joined to a turbine by a core rotor, with a combustor disposed therebetween for receiving compressed air from the compressor and fuel through a valve for producing combustion gas discharged to the turbine. A speed sensor measures speed of the core rotor, and a pressure sensor measures pressure at an inlet to the compressor. A controller is operatively joined to the sensors and the fuel valve and is configured for limiting fuel flow to the combustor in response to core acceleration rate and compressor inlet pressure to limit transient temperature of the combustor discharge combustion gas.

REFERENCES:
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patent: 4470118 (1984-09-01), Morrison
patent: 4490791 (1984-12-01), Morrison
patent: 4581889 (1986-04-01), Carpenter et al.
patent: 4593523 (1986-06-01), Hawes
patent: 4815928 (1989-03-01), Pineo et al.
General Electric, "Aircraft Gas Turbine Guide," Apr. 1972, pp.: cover, back, 1-39 to 1-49.
Traeger, "Aircraft Gas Turbine Engine Technology," 1979, pp.: cover, i, ii, 211-215 and 228-232.
GE Aircraft Engines, "F414-GE-400, Low Rate Production I," Proposal 95-RNM-25, 31 Mar. 95, cover only.
GE Aircraft Engines, "F414-GE-400, Preliminary Flight Qualification Test Phase," R95AEB004, 24 Jul. 95, cover and p. 2, and 21 Jul. 95 cover letter .

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