General Electric Company

George Raymond Hubschmitt

David Anthony DeAngelis

Thomas Edward Wickert

Malath Ibrahim Arar

Howard Jay Kaplan

Kevin Joseph Prowse

Henry G Chu

James Giles Eignor

Timothy Robert Kemp

Scott V Annin

Brian P Ray

A positive displacement pump supplies a low lubricity liquid fuel through a main supply line to the combustors of a turbine. A pressure transducer and a flow meter are provided in the main fuel supply line. The fuel is supplied to a pressure compensated fuel delivery valve which divides the fuel equally among the combustors and affords pressure compensation. A controller is responsive to the pressure in the main fuel supply line to control a bypass pressure valve to supply fuel in the main supply line at a predetermined pressure. The controller also controls the total volume of fuel flow rate through the pressure compensated fuel delivery valve responsive to the flow meter. In another form, a centrifugal pump supplies fuel to the pressure compensated fuel delivery valve. A controller responsive to the flow meter in the main supply line controls the total fuel flow rate to the valve which divides the fuel equally among the combustors at equal flow rates.

Pressure compensated fuel delivery system for the combustors of

The high pressure inlet bleed heat system includes a plurality of tubes which receive heated compressed air from the compressor extraction discharge manifold. The tubes extend into the inlet duct of the compressor, are uniformly spaced one from the other and have a uniform distribution of laterally opening apertures along their lengths in registration with the apertures of next laterally adjacent tubes. The tubes are located downstream of the silencer baffles. By providing choked flow through the apertures and lateral registration of the apertures of adjacent tubes, complete mixing of the heated air with the inlet air vortices behind the silencer baffles is achieved, affording a uniform temperature distribution across the inlet duct with minimum pressure loss. The tubes are constructed to accommodate thermal expansion of the manifold receiving compressor discharge air, the manifold also being supported to accommodate thermal expansion and contraction.

High pressure inlet bleed heat system for the compressor of a turbine

A trip oil system automatically controls the fuel shut-off valves in an industrial gas turbine. The trip oil system applies hydraulic pressure to actuate and hold open a fuel shut-off valve so that fuel flows to the combustor of the gas turbine. When the trip oil system relieves the hydraulic pressure, the fuel shut-off valve closes and stops the fuel flow to the combustor. A bank of three solenoid valves controls the application of hydraulic pressure to each fuel shut-off valve. Hydraulic fluid conduits interconnect the three solenoid valves such that no single valve by itself can relieve the hydraulic pressure applied to the fuel shut-off valve. During normal operation of the gas turbine, all three redundant solenoid valves are activated. For the trip oil system to cause the fuel shut-off valve to close, at least two of the solenoid valves must de-energize to relieve pressure to the fuel shut-off valve.

Redundant trip solenoid valve shut-off for gas turbine fuel system

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Ballston Lake, NY, United States of America

George Raymond Hubschmitt