Honeywell International Inc.

Alliedsignal Inc.

Cristopher Frost

Yogendra Y Sheoran

Shakeel Nasir

Nick A Nolcheff

Yates Wong

Ly D Nguyen

Zedic Daniel Judd

Jennifer Ann Reich

Richard D Kocher

Jason Smoke

Bruce Dan Bouldin

Eric Bridges

Marc Schmittenberg

Doug Hollingshead

John Schugardt

Mingfong Hwang

Todd A Kincheloe

James Laffan

Michael Stephen Crestin

Donald G Godfrey

Bradley Reed Tucker

Ian L Critchley

David Chou

Mahmoud Mansour

Christopher Zollars

John Taylor Pearson

Stony Kujala

Hans Heydrich

Robert B Sumegi

Ed Zurmehly

Ronald B Pardington

David G Walhood

Eduardo Guerra

Patrick Flynn

Lori Wheeler

Jeff Guymon

Mike O'Brien

Daniel Aukland

Ronald P Maty

Barry J Kingery

Clay R Johnstun

Michael O'Brien

Justin Brown

Hakan Aksoy

John M Wait

Matt Greenman

Mariee Hayden

Daih-Yeou Chen

Carlos Enrique Murrieta

Jason Vizcaino

Jennifer Battista

Victor Cabilan

Mary Eileen Richardson

Yogendra Yogi Sheoran

Marieé Hayden

A fluid level sensor for sensing a level of a fluid within a toroid-shaped tank includes a float ring, a float structure, a gauge shaft, and a tiller arm. The float ring rotate s within the toroid-shaped tank about a first rotational axis. The float structure exhibits buoyancy in the fluid disposed within the toroid-shaped tank and supplies a force to the float ring based on the level of the fluid within the toroid-shaped tank. The gauge shaft is mounted for rotation about a second rotational axis and rotates about the second rotational axis to a position representative of the level of the fluid within the toroid-shaped tank. The tiller arm supplies the rotational drive force to the gauge shaft when the float ring rotates.

Fluid level sensor for a toroid-shaped tank

A method for scavenging small particles from a turbine engine includes directing compressed air through a flowpath, downstream of a compressor, which causes a reduction in a radial flow component and the introduction of or an increase in an axial flow component of the compressed air, removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flowpath, and returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum. Further, the method includes removing the majority of small particles from the plenum. The step of removing occurs intermittently during engine operation, during engine shutdown, or while the engine is not in operation, but does not occur continuously during engine operation.

Scavenge methodologies for turbine engine particle separation concepts

High performance wedge diffusers utilized within compression systems, such as centrifugal and mixed-flow compression systems employed within gas turbine engines, are provided. In embodiments, the wedge diffuser includes a diffuser flowbody and tapered diffuser vanes, which are contained in the diffuser flowbody and which partition or separate diffuser flow passages or channels extending through the flowbody. The diffuser flow channels include, in turn, flow channel inlets formed in an inner peripheral portion of the diffuser flowbody, flow channel outlets formed in an outer peripheral portion of the diffuser flowbody, and flow channel throats fluidly coupled between the flow channel inlets and the flow channel outlets. The diffuser vanes include a first plurality of vane sidewalls, which transition from linear sidewall geometries to non-linear sidewall geometries at locations between the flow channel inlets and the flow channel outlets.

High performance wedge diffusers for compression systems

Circumferentially-split diffuser assemblies utilized within compression systems, such as centrifugal and mixed-flow compression systems employed within gas turbine engines, are provided. In embodiments, the diffuser assembly includes flow passages, which extend through the diffuser assembly and which include diffuser flow passage sections. Diffuser airfoils are interspersed with the diffuser flow passage sections. The diffuser airfoils include inboard and outboard airfoil segments distributed around a diffuser assembly centerline. The inboard and outboard airfoil segments are contained in and, thus, defined by inner and outer annular diffuser structures, respectively. The outer annular diffuser structure circumscribes the inner annular diffuser structure. In certain cases, the inboard airfoil segments and at least a portion of inner annular diffuser structure are composed of a first material, while the outboard airfoil segments and at least a portion of outboard annular diffuser structure are composed of a second material different than the first material.

Diffuser assemblies for compression systems

An inertial inlet particle separator system for a vehicle engine is provided. A separator assembly and collector assembly are coupled to the scavenge flow path and configured to receive the scavenge air. The collector inlet has a throat defining a cumulative throat area at each position along the throat length from the first throat end to the second throat end. The collector body defines a cross-sectional area associated with each position along the throat length between the first throat end and the second throat end. The collector outlet is coupled to the collector body such that scavenge air flows into the collector inlet, through the collector body, and out through the collector outlet. At a first position between the first throat end and the second throat end, the respective cross-sectional area of the collector body is greater than or equal to the respective cumulative throat area.

Inlet particle separator systems and methods

Provided is a radial diffuser that includes a housing, a plurality of diffuser vanes, and a plurality of deswirl vanes and at least one vane extension providing a service routing. Each of the vane extensions is disposed after a radial section and may extend into or through a transition and into the deswirl cascade. At least a portion of the vane extensions include a service passage extending therethrough. Each service passage is configured to allow a service conduit to extend therethrough without adversely crossing either a diffusion flow passage or a transition flow passage.

Service routing configuration for a gas turbine engine diffuser system

A multi-channel particle separator includes a plurality of vanes. Each vane is spaced apart from at least one other adjacent vane to define a flow channel, and includes a leading edge, a trailing edge, a first side wall, a second sidewall, and a splitter. The first side wall extends between the leading edge and the trailing edge. The second side wall is spaced apart from the first side wall and extends from the leading edge toward the trailing edge. The splitter may be rotationally coupled to the trailing edge and extend toward the leading edge. The splitter is spaced apart from the first side wall to define a scavenge volume and is rotatable between an extended position and a retracted position. The vanes may also or instead be coupled to a ring-shaped structure.

Multi-channel particle separator

An accessory gear box for a gas turbine engine having a drive shaft with a rotational axis and a tower shaft coupled to the drive shaft is provided. The accessory gear box includes a first plurality of gears arranged, which extend along a first axis substantially parallel to the rotational axis of the drive shaft. The accessory gear box includes a second plurality of gears, which extend along a second axis. The accessory gear box includes a first shaft, with one of the first plurality of gears coupled to the first shaft, and one of the second plurality of gears coupled to a second shaft. The one of the second plurality of gears coupled to the first shaft includes a first engagement surface and a second engagement surface, and the second engagement surface is coupled to another one of the second plurality of gears to drive the second shaft.

Transverse mounted accessory gearbox

A tie shaft for a rotating group of an engine core includes a cylindrical body having an internal surface and an external surface and extending between a forward end and an aft end. The tie shaft further includes a first group of internal grooves on the internal surface of the cylindrical body proximate to the forward end and a second group of internal grooves on the internal surface of the cylindrical body proximate to the aft end.

Gas turbine engines with internally stretched tie shafts

Thermal isolating service tubes and assemblies thereof for gas turbine engines are provided. The thermal isolating service tube comprises an inner tubular member defining a fluid passage and at least one outer tubular member disposed about the inner tubular member. A spacing volume is defined between at least the inner tubular member and an adjacent outer tubular member. The thermal isolating service tube comprises a unitary structure and has at least one portion with a curved configuration, a non-circular cross-sectional shape, or both.

Thermal isolating service tubes and assemblies thereof for gas turbine engines

A gas turbine engine and an accessory gear box (AGB) are provided for. The gas turbine engine comprises a drive shaft, a compressor, a combustor and an exhaust turbine, where the exhaust turbine and the compressor are coaxially connected by the drive shaft. The gas turbine engine further comprises an engine casing of varying diameters circumferentially enveloping the compressor, the combustor and the exhaust turbine with a waist located between the compressor and the combustor. The gas turbine engine also includes an accessory gear box (AGB) attached to the engine casing at the waist, the AGB comprising a gear rotating on an axis extending in a transverse direction relative to that of the drive shaft.

A generator having an integral oil tank for an auxiliary power unit (APU) is provided. A gas turbine engine has a turbine shaft extending from an aft portion to a forward portion where it is in communication with a gear box mounted thereto. The gearbox advantageously has at least one oil gravity drain passage in flow communication with a lower portion thereof and is suitable for reducing the speed of the turbine shaft by gear reduction to power an oil cooled generator attached thereto. The oil cooled generator has at least one oil gravity drain passage therein. An engine oil tank is integral with and advantageously removable from the generator and is in flow communication with each oil gravity drain passage making is suitable for gravity scavenging oil from the generator and advantageously the gearbox.

Gravity scavenged generator with integral engine oil tank

A compressor scroll is provided for redirecting an airflow from a compressor. The compressor scroll includes a spiral-shaped body; a radial inlet formed in the body for receiving the airflow from the compressor as inlet airflow; and an outlet formed in the body such that inlet airflow flows through the body and exits the outlet as outlet airflow, with at least a portion of the outlet airflow crossing at least a portion of the inlet airflow.

Compressor scrolls for auxiliary power units

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Scottsdale, AZ, United States of America

Cristopher Frost