General Electric Company

John Clisby Blanton

Paul H Kutschenreuter, Jr

Alston Ilford Scipio

Sanji Ekanayake

David Martin Johnson

Anthony Holmes Furman

Joseph Philip Klosinski

Kenneth Edward Seitzer

John David Bibler

Matthew Ryan Ferslew

William Carl Ruehr

Seung-Woo Choi

Kenneth Jay Moore

Narendra Are

James Carlton Dudley

Kenneth Dale Moore

James Warren Hackler

Jason Corey Slagle

Jansen James Litter

Meiyun Li

Scott J Dennison

Robert N Pittman

Stephen P Schrantz

Robert J Maffeo

Mir M Ali

Jared Stephan Ashley

The present application provides an inlet bleed heat control system for a compressor of a gas turbine engine. The inlet bleed heat control system provides an inlet bleed heat manifold and an ejector in communication with the inlet bleed heat manifold such that the ejector is in communication with a flow of compressor discharge air and a flow of ambient air.

Inlet bleed heat control system

A rotor wheel for a gas turbine rotor has a first side having a plurality of curved paddles separated by a plurality of curved slots and a second side having a plurality of radial paddles separated by a plurality of radial slots. A method of purging a rotor of a gas turbine includes providing a flow of compressed air between adjacent rotor wheels of the rotor in a radially downward direction on a first side of each wheel and in a radially upward direction on a second side of each wheel; passing the flow through a curved slots on the first side of each rotor wheel; and passing the flow through radial slots on the second side of each rotor wheel.

Apparatus and method for purging a gas turbine rotor

A sensor assembly includes a housing and a tube. The housing has a first leading edge portion which is capable of being located in a compressor/fan inlet flow path and which includes an interior wall section. The tube has a proximal portion including an air inlet which is adapted to receive a compressor bleed air flow and a distal portion which is located in the housing and which includes at least one air outlet hole. The hole is spaced apart from the interior wall section and is aligned to direct at least some compressor bleed air flow to impinge against the interior wall section. The housing includes an opening which receives air from the flow path when the housing is located in the flow path, wherein the opening is adapted for fluid communication with a sensor, and wherein the sensor measures at least one of air temperature and air pressure.

Temperature and/or pressure sensor assembly

An integrated engineering analysis system that determines at least one final output value in response to at least one initial input value. A first subprocesses provides at least one output value in response to the initial input value. A plurality of subprocesses provide a plurality of output values in response to the output values of the first subprocess. The plurality of output values and the output value of the first subprocess are inputted into at least one of the plurality of subprocesses. A command code executes each of the plurality of subprocesses in response to the output values and determines which one of the plurality of subprocesses to run and a final subprocess provides a final output. The final output is the result of a plurality of calculations executed by the plurality of subprocesses and the command code compares the final output with the initial input.

Integrated engineering analysis process with solution feedback

A scramjet engine is disclosed which is effective for use in a hypersonic aircraft as an aircraft-integrated scramjet engine. The engine includes a first surface having an aft facing step, and a cowl upper surface spaced from the first surface to define an integrated inlet-combustor therebetween. A method of operating the engine includes injecting fuel into the inlet-combustor at the step for mixing fuel with supersonic airflow for generating supersonic combustion gases in the inlet-combustor. In the preferred embodiment of the invention, the fuel is injected to create a fluid boundary defining a subsonic fuel zone and a supersonic fluid zone. The fluid boundary is variable and eliminates start and unstart problems requiring variable inlet geometry in a conventional scramjet engine.

Method of operating a scramjet including integrated inlet and combustor

A scramjet engine is disclosed which is effective for use in a hypersonic aircraft as an aircraft-integrated scamjet engine. The engine includes a first surface having an aft facing step, and a cowl upper surface spaced from the first surface to define an integrated inlet-combustor therebetween. Means for injecting fuel into the inlet-combustor at the step are provided for mixing fuel with supersonic airflow for generating supersonic combustion gases in the inlet-combustor. In the preferred embodiment of the invention, the fuel injecting means is effective for injecting fuel to create a fluid boundary defining a subsonic fuel zone and a supersonic fluid zone. The fluid boundary is variable and eliminates start and unstart problems requiring variable inlet geometry in a conventional scramjet engine.

Scramjet including integrated inlet and combustor

A method for feeding an extrudable fuel into a pressurized combustion chamber includes extruding the fuel through a screw extruder and introducing the extruding fuel into the chamber through a passage at the end of the extruder. The passage has reduced cross-sectional area compared to that of the extruder, so that extruded fuel is compacted and provides a pressure seal for the chamber. The compacted fuel is atomized as it is introduced into the combustion chamber, so that the fuel is broken up into particles and dispersed into the chamber. Apparatus for carrying out the invention includes a screw extruder having a helically shaped screw of constant radius affixed to the outer surface of a rotatable shaft. A frusto-conically shaped member is attached to the end of the shaft and disposed through the end of the extruder so that an annular opening is defined between the outer surface of the member and the inner surface of the extruder body. The apparatus also includes an atomizing gas channel for directing an atomizing gas against compacted fuel as it is introduced into the combustion chamber.

Method and apparatus for feeding an extrudable fuel to a pressurized

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Simpsonville, SC, United States of America

John Clisby Blanton