Hamilton Sundstrand Corporation

Sundstrand Corporation

United Technologies Corporation

Solar Turbines Inc.

Other

Pratt & Whitney

James C Napier

Jay Francisco

Anthony C Jones

Robert G Thompson

Arthur G Metcalfe

William A Compton

Farooq Rehman

Behzad Hagshenas

Gordon F Jewess

Eric J Alexander

Scott A Liljenberg

David R Polak

Eric Andrew Nager

Jeffrey Carl Brill

Ray-Sing Lin

Robert Hans Schlinker

Dan G Sapiro

Robert W Fawley

James J McLaughlin

Krzysztof Kowiel

Agata Miaskiewicz

Wayne A Johnson

Stanley C Mickaelian

Navindaran Sirinivasan

Marek Michalik

Jay M Francisco

An inlet door for an auxiliary power unit includes a door body with opposed interior and exterior surfaces. The interior surface of the inlet door is curved to diffuse sound waves received by the interior surface.

Acoustically diffusive auxilary power unit inlet doors

An exhaust system for an APU in a gas turbine engine aircraft having a tail cone in which exhaust noise is reduced. An APU exhaust liner is attached to the APU and extending to an oval cutout at the tail cone The liner has a first constant cross section from the APU to a point proximate the tail cone, and a second, increasing cross section from the point proximate the tail cone to the liner cutout. The liner is turned toward the side of the tail. The liner cutout is further enlarged with at least one larger cutout.

APU exhaust system

A retainer for a gas turbine engine includes a center body, a plurality of struts, and a ring. The plurality of struts are connected to and extend outward from the center body. The ring is connected to the plurality of struts and is positioned aft of the center body with respect to a direction of airflow through the gas turbine engine.

Turbine hub retainer

An air inlet assembly comprising an entrance region configured to receive an airflow, an exit region configured to output the airflow, and an attenuation region disposed between the entrance region and the exit region. The attenuation region has a cross section aspect ratio of at least about 5-to-1, and comprises acoustic absorbing material.

Air inlet noise attenuation assembly

An exemplary diffuser includes a plurality of air flow channels defined by a corresponding plurality of vanes. The vanes extend from a first side of the diffuser and define a width of the air flow channel between the corresponding plurality of vanes. The first side has at least one tapered surface extending from an inner radial position to an outer radial position. The distance between a tapered surface and a top side of the plurality of the vanes defines a depth of the air flow channel. The width of the air flow channel varies relative to the depth of the air flow channel along the length of the air flow channel.

Gas turbine engine diffuser having air flow channels with varying widths

An example auxiliary power unit air inlet assembly includes a noise attenuating component disposed within a conduit. The conduit is configured to communicate a first flow of fluid to an auxiliary power unit. A second flow of fluid is communicated to the noise attenuating component. The second flow of fluid limits formation of ice in the conduit. The first flow of fluid is different than the second flow of fluid.

Arrangement for maintaining flow to an air inlet of an auxiliary power unit assembly

An exhaust silencer assembly includes an exhaust duct and an exhaust silencer. The exhaust silencer is disposed about the exhaust duct and has a plurality of solid baffles and at least one perforated baffle The exhaust silencer assembly is disposed downstream of an auxiliary power unit and at least partially attenuates the downstream noise of the combustion gases that result from operation of the auxiliary power unit. In one embodiment, at least one of the plurality of solid baffles is disposed to extend axially between generally radially extending solid baffles, perforated baffle(s), or partially perforated baffles. The axially extending solid baffle allows for cavity depth variation in the silencer to optimize tuning of particular frequencies from the auxiliary power unit.

Exhaust silencer with baffles

An exhaust duct system for a gas turbine engine that mounts within a tail cone of an aircraft, comprises an exhaust exit that exits one side of the tail cone offset from the axial centerline of the tail cone and an exhaust duct that couples the engine to the offset exhaust exit, with a straight section of the exhaust duct extending from the exhaust exit for a length that corresponds to at least one diameter of the exhaust duct.

Low noise exhaust ducting system

A system for reducing compressor noise includes a rotor having a plurality of blades. The blades have a nominal geometry characterized by a blade parameter. At least some of the blades are mistuned, such that they differ from the nominal geometry by greater than a manufacturing tolerance in the blade parameter. The blades produce shock waves at a blade passing frequency, and the mistuned blades shift acoustic energy away from the blade passing frequency to multiple lower amplitude tones at other frequencies. The system is configurable to be deployed with an inlet silencer that preferentially absorbs acoustic energy at some of the shifted frequencies.

System for reducing compressor noise

An inlet duct for an auxiliary power unit comprises an inlet end, and extends to an outlet end. At least one splitter is positioned within the duct and between the inlet and the outlet end to sub-divide an interior of the duct into plural flow paths.

Auxiliary power unit inlet duct with acoustic silencing

An exhaust silencer assembly comprising a casing having an exhaust gas entrance opening, an exhaust gas exit opening, and a cooling air inlet opening, and an acoustic-attenuating porous liner disposed within an interior chamber of the casing, thereby dividing the interior chamber into an inner region located between the exhaust gas entrance opening and the exhaust gas exit opening, and an outer region located between the acoustic-attenuating porous liner and the casing, where the cooling air inlet opening is located at the outer region.

Mixed-flow exhaust silencer assembly

A method of measuring the presence of oil in turbine bleed air that uses an aerosol sampler/size classifier to do a comparative measurement of the engine bleed air to the ambient air entering the engine on a real time basis by comparing quantity and size distribution of suspended particles of engine inlet air with suspended particles in the bleed air throughout the normal operating schedule of the engine and determining the presence of oil in the bleed air when the quantity and size distribution of suspended particles in the bleed air exceeds the quantity and size distribution of suspended particles in the engine inlet air by a predetermined amount.

Detection of oil in turbine engine bleed air

In order to reduce noise transmission through the air inlet duct (16) of a turbine engine (10), the air inlet duct (16) provides a non-linear path defined by a bend (24) for air from a source, and the turbine engine (10) includes a sound attenuation assembly (26) in the form of a splitter dissipative silencer disposed near the bend (24) in the air inlet duct (16). More specifically, the turbine engine (10) is such that the splitter dissipative silencer (26) can be formed as a modular assembly (42) removably securable near the bend (24) in the air inlet duct (16) upstream of a radial compressor (12) for removal and/or replacement or availability as an optional component of the turbine engine (10).

Turbine inlet silencer

An abradable coating is provided for use on a composite substrate which has a coefficient of thermal expansion substantially similar to that of the substrate and which is formed with a matrix resin of the same type of resin used to form the substrate. In particular, with a composite substrate formed from carbon or graphite fibers impregnated with a polyimide resin, an abradable coating formed from carbon or glass microballoons in a polyimide resin matrix has been found to avoid delamination as a result of thermal cycling between -65.degree. F. and 500.degree. F. Accordingly, that abradable coating is particularly suitable for use with composite compressor shrouds in gas turbine engines and aircraft auxiliary power units.

Growing community of inventors

San Diego, CA, United States of America

James C Napier