United Technologies Corporation

Raytheon Technologies Corporation

Pw Power Systems, Inc.

Rtx Corporation

Charles C Wu

Russell J Bergman

Kevin N McCusker

Brett Alan Bartling

Tracy A Propheter-Hinckley

John J Korzendorfer

David Frederick Glasspoole

John H Mosley

Fabian D Betancourt

James P Chrisikos

Roger Gates

Gavin Hendricks

Henry K Webster

Andrew P Boursy

Fernando K Grant

Roger E Paolillo

Christopher William Moore

John J O'Connor

Alexander Sankovich

Page Russell Palmiter

Nils G Dahl

Kevin M Plante

Christopher J Loconto

Mark S Turner

David Glasspoole

A vane comprises an airfoil extending from a radially outer platform to a radially inner platform. A pair of legs extend radially inwardly from the radially inner platform, and an air flow passage extends through the radially outer platform, through the airfoil, and into a chamber defined between the pair of legs. One of the pair of legs includes a plurality of injector holes, configured to allow air from the radially outer platform to pass outwardly of the holes. A gas turbine engine is also disclosed.

Multiple injector holes for gas turbine engine vane

A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.

Gas turbine engine turbine impeller pressurization

A power turbine section for a gas turbine engine includes a heat shield assembly mounted to a bearing support, the heat shield assembly forms an outer diameter directed toward an inner vane platform of the power turbine vane array.

Power turbine heat shield architecture

According to an embodiment disclosed herein, an apparatus for cooling a rotating part having cooling channels therein, the rotating part attaching to a disk rotating about an axis, the disk having a conduit for feeding a cooling fluid to the cooling channel is described. The apparatus has a first impeller rotating with the disk and in register with the conduit and an outer periphery of the disk, the impeller directing the cooling flow to the conduit.

High solidity and low entrance angle impellers on turbine rotor disk

A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a control pocket defined between a radially inner surface and a spaced radially outer surface. The control pockets and their associated knife edge seals create a difficult flow path to prevent leakage into radially inner portions of the turbine section.

Gas turbine engine with canted pocket and canted knife edge seal

Cooling air manifold splash plates and gas turbine engine systems involving such splash plates are provided. In this regard, a representative cooling air manifold splash plates includes: a base having an aperture; and an air deflector supported by the base, the air deflector being positioned relative to the base to receive, from the aperture, a radial flow of gas turbine engine cooling air, the air deflector being operative to redirect at least some of the air received circumferentially.

Cooling air manifold splash plates and gas turbines engine systems involving such splash plates

A turbo machine includes a housing having a bearing compartment for receiving lubrication. The housing also provides a buffer compartment for receiving air, for example, compressor bleed air. A turbine shaft is supported within the housing on a bearing for rotation relative to the housing. The bearing is arranged within the bearing compartment. A seal is arranged between the turbine shaft and the housing and separates the bearing and buffer compartments. The seal includes opposing lubrication and air sides that are respectively exposed to the bearing and buffer compartments. The buffer tube is fluidly connected to a body of the buffer compartment. A buffer tube introduces flow generally tangential to an inner surface of the body for generating a swirl within the body. The buffer tube includes a velocity control device such a venturi arranged at an exit of the tube to control the velocity of the flow entering the body. An orifice plate is arranged upstream from the venturi to control the flow to a desired flow rate. The swirling flow within the body at the desired flow rate and velocity provides a uniform pressure gradient at idle having a large enough pressure magnitude to create the desired pressure differential across the seal. The increased pressure in the buffer compartment in the vicinity of the seal prevents leakage of lubricant past the seal at idle.

Flow delivery system for seals

Growing community of inventors

Glastonbury, CT, United States of America

Charles C Wu