General Electric Company

The United States of America As Represented by the Administrator of the

William Carl Ruehr

Alan Roy Stuart

Robert Paul Czachor

Daniel Edward Mollmann

Ambrose A Hauser

Gert Johannes Van Der Merwe

Michael Harvey Schneider

Jay L Cornell

Leroy H Smith, Jr

John Clisby Blanton

Thomas Richard Henning

Jack D Wright

Sunil Kumar Sinha

Jason Corey Slagle

James Warren Hackler

James L Younghans

Edwin B Smith

Charles R Vanfleet

Meiyun Li

Jansen James Litter

Jared Stephan Ashley

A method for assembling a rotor assembly and a rotor assembly are provided. The method comprises providing a rotor blade including a first sidewall, a second sidewall, where the first and second sidewalls are connected at a leading edge and a trailing edge and extend in span from a root portion to a tip portion, removing blade material from the tip portion to form a tip portion rake angle that enables the tip portion to extend obliquely between the first and second sidewalls, and coupling the rotor blade to a shaft such that during tip rubs the tip portion rake angle facilitates reducing radial loading induced to the blade during tip rubs.

Methods and apparatus for fabricating a rotor assembly

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

A method and apparatus for assembling a rotatable machine is provided. The machine includes a plurality of blades that extend radially outwardly from a rotor. The method includes determining a moment weight of each blade in a row of blades, determining a geometric parameter of each blade in the same row of blades, and determining a mapping order of each blade using the moment weight and the geometric parameter. The apparatus includes a computer system that includes a software product code segment for minimizing imbalance in a bladed rotor wherein the segment is configured to receive a moment weight value for each blade to be installed in said rotor, receive a geometric parameter value for each blade to be installed in said rotor, calculate a blade location on the rotor based on the received values, and generate a blade map based on the calculated location.

Methods and apparatus for assembling rotatable machines

A casing for the fan section of an aircraft gas turbine engine of the turbofan type. The casing includes an inner filler material and is defined by an outer shell and an inner liner that is spaced radially inwardly from the outer shell. The inner liner is held in position relative to the outer shell by a plurality of radially-inwardly-extending support pins. The pins are carried by the outer shell and are slidably received in and extend at least partially into the inner liner. The support pins retain the inner liner against axial and rotational movement relative to the outer shell, while allowing relative radial movement therebetween in response to thermal expansion and contraction, as well as in response to aircraft maneuver loads imposed on the engine.

Fan casing liner support

Aircraft engine or similar article

An inlet for a gas turbine engine is disposed about a curved centerline for the purpose of accepting intake air that is flowing at an angle to engine centerline and progressively turning that intake airflow along a curved path into alignment with the engine. This curved inlet is intended for use in under-the-wing locations and similar regions where airflow direction is altered by aerodynamic characteristics of the airplane. By curving the inlet, aerodynamic loss and acoustic generation and emission are decreased.

Curved centerline air intake for a gas turbine engine

A method and apparatus are disclosed for limiting ingestion of debris into the inlet of a gas turbine engine. The invention includes providing first means in communication with a source of fluid under pressure for introducing at least one jet of fluid at a point aft of the leading edge of a nacelle associated with the engine inlet. The first means are adapted to discharge the fluid jet away from the leading edge and in the aft direction to establish a low pressure region aft of the leading edge and in sufficient proximity to a second vortex formation region so as to draw airflows from the second region into the low pressure region and away from the engine inlet.

Method and apparatus for limiting ingestion of debris into the inlet of

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Cincinnati, OH, United States of America

William Carl Ruehr