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Gas Turbine Engine

Gas Turbine Engine-related patent applications - as published by the U.S. Patent and Trademark Office (USPTO).


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Light weight swirler for gas turbine engine combustor and a method for lightening a swirler ...
United Technologies Corporation
August 10, 2017 - N°20170227226

The disclosure is directed to a swirler body for a combustor of a gas turbine engine, where the swirler body includes an annular mount face which defines at least one pocket. The disclosure is directed to a swirler assembly for a combustor of a gas turbine engine, where the swirler assembly includes a swirler first body with an annular first ...
Film cooling hole arrangement for acoustic resonators in gas turbine engines
Siemens Aktiengesellschaft
August 10, 2017 - N°20170227220

The present disclosure provides a gas turbine combustor liner (34) comprising an outer surface (38) and an inner surface (36), a plurality of film cooling holes (44) through a thickness of the gas turbine combustor liner (34), and a plurality of resonator boxes (32) affixed to the outer surface (38) of the gas turbine combustor liner (34). The film cooling holes (44) extend circumferentially around the gas turbine combustor ...
Flange joint assembly for use in a gas turbine engine
General Electric Company
August 10, 2017 - N°20170227152

A flange joint assembly includes a first structure including a first flange and a second structure including a second flange coupled to the first flange to form a joint therebetween. The second flange includes a radially outer surface. The flange joint assembly also includes a compression ring coupled to at least the radially outer surface and configured to apply a ...
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Gas Turbine Engine Patent Applications
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Turbine engine compressor blade
General Electric Company
August 10, 2017 - N°20170227016

An airfoil for a compressor blade of a gas turbine engine has a chord between a leading edge and a trailing edge and a span between a root and a tip. The airfoil can further include a reduction in local chord from about 75% span to the tip for about a 5% reduction in local solidity. The airfoil can have decreasing sweep ...
Systems and methods for reducing friction during gas turbine engine assembly
United Technologies Corporation
August 10, 2017 - N°20170227014

Systems and methods for reducing friction during gas turbine engine assembly may comprise, a rear hub which may comprise a conical web, a horizontal arm coupled to the conical web, and/or a hub kickstand coupled to the conical web. The conical web, horizontal arm, and/or hub kickstand may converge at a pivot point. The hub kickstand may be ...
Alignment system and methodology to account for variation in a gas turbine engine
United Technologies Corporation
August 10, 2017 - N°20170226964

A gas turbine engine includes a bushing that is non-round in cross-section, the bushing receivable within an aperture. A fastener passes through the bushing to retain a second component to a third component with respect to the first component.
Gas Turbine Engine Patent Pack
Download 1617+ patent application PDFs
Gas Turbine Engine Patent Applications
Download 1617+ Gas Turbine Engine-related PDFs
For professional research & prior art discovery
inventor
  • 1617+ full patent PDF documents of Gas Turbine Engine-related inventions.
  • Exact USPTO filing data with full-text, images, drawings & claims.
  • Index pages: Table View and Image-Grid View layouts. All images in each PDF.
Geared architecture for high speed and small volume fan drive turbine
United Technologies Corporation
August 10, 2017 - N°20170226935

A gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan rotor. Aspects of the gear system are provided with defined flexibility. The fan drive turbine has a first exit area and rotates at a first speed. A second turbine section has a second exit area and rotates at a ...
Bearing outer race retention during high load events
General Electric Company
August 10, 2017 - N°20170226927

A retention housing for the outer race of a bearing of a gas turbine engine includes a spring finger housing connected to and overlying a bearing housing that is connected to the outer race of the bearing. The spring finger housing includes an arrangement of spring fingers that yields a lightweight housing capable of withstanding very high radial loads combined ...
Bearing outer race retention during high load events
General Electric Company
August 10, 2017 - N°20170226894

A retention housing for the outer race of a bearing of a gas turbine engine includes a spring finger housing connected to and overlying a bearing housing that is connected to the outer race of the bearing. The spring finger housing includes an arrangement of spring fingers that yields a lightweight housing capable of withstanding very high radial loads combined ...
Method for clearance control in a gas turbine engine
United Technologies Corporation
August 10, 2017 - N°20170226886

A gas turbine engine, system, and method with clearance control are provided. For example, the gas turbine engine includes a static component, and a rotating component that shifts axially in one of an aft direction and a forward direction in relation to the static component during a first operating condition of the gas turbine engine, and shifts axially in the ...
Gas turbine engine with a rim seal between the rotor and stator
General Electric Company
August 10, 2017 - N°20170226884

An apparatus relating to a rim seal for gas turbine engine comprising a wing extending into a buffer cavity with at least one set of protuberances including a first protuberance extending into the buffer cavity and a second protuberance extending from the wing into the buffer cavity, with the first and second protuberances being axially spaced from each other.
Gas turbine engine with a cooling fluid path
General Electric Company
August 10, 2017 - N°20170226882

An apparatus and method of a gas turbine engine comprising a rotor having at least one disk with a rotor defining an axial face and a stator having at least one ring with a stator axial face confronting the rotor axial face, with terminal portions of the axial faces forming a fluid outlet there between. A recess formed in one ...
Chordal seal with sudden expansion/contraction
United Technologies Corporation
August 10, 2017 - N°20170226876

A static component for a gas turbine engine includes an axially extending body comprising a forward end and an aft end disposed axially downstream from the forward end. A rib is formed on at least one of the forward end and the aft end of the axially extending body and extending axially from the axially extending body. A recess is ...
Gas Turbine Engine Patent Pack
Download 1617+ patent application PDFs
Gas Turbine Engine Patent Applications
Download 1617+ Gas Turbine Engine-related PDFs
For professional research & prior art discovery
inventor
  • 1617+ full patent PDF documents of Gas Turbine Engine-related inventions.
  • Exact USPTO filing data with full-text, images, drawings & claims.
  • Index pages: Table View and Image-Grid View layouts. All images in each PDF.
Gas turbine engine airfoil
General Electric Company
August 10, 2017 - N°20170226868

An apparatus and method of cooling a tip of an airfoil for a gas turbine engine, includes a rib circumscribing the tip to define a tip plenum. A tip baffle partially divides the tip plenum, being spaced from the rib by a baffle slot. The rib includes a tip slot in fluid communication with the baffle slot to provide a ...
Frangible gas turbine engine airfoil
General Electric Company
August 10, 2017 - N°20170226867

An airfoil for an aircraft engine is provided. The airfoil may include a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base. The airfoil may include at least one discontinuous ply having a first ply segment, a second ply ...
Balancing of axial thrust forces within a gas turbine engine
Rolls-royce Plc
August 10, 2017 - N°20170226859

A thrust balancing mechanism for balancing axial loads on a rotor thrust bearing 3 is described. The mechanism comprises a piston arrangement 6 axially mounted on a stationary structure 2, about a centre axis arranged, in use, in coaxial alignment with a rotating shaft 1 carrying the rotor thrust bearing 3. A hydrodynamic thrust bearing 8 is mounted, in use, between the piston 6 and the rotor ...
Torsional damping for gas turbine engines
General Electric Company
August 03, 2017 - N°20170222518

The present disclosure is directed to a gas turbine engine assembly having a compressor configured to increase pressure of incoming air, a combustion chamber, at least one turbine coupled to a generator, a torsional damper, and a controller. The combustion chamber is configured to receive a pressurized air stream from the compressor. Further, fuel is injected into the pressurized air ...
Single-axis inspection scope with bendable knuckle and method for internal inspection of power generation machinery
Siemens Energy, Inc.
August 03, 2017 - N°20170219815

Internal components of power generation machinery, such as gas turbine engines, are inspected with a spherical, optical-camera inspection system, mounted within a camera housing on a distal end of a compact diameter, single-axis inspection scope. The inspection scope includes nested, non-rotatable telescoping tubes, which define an extension axis. Circumscribing, telescoping tubes have anti-rotation collars, which are in sliding engagement with ...
Single-axis inspection scope with anti-rotation extension and method for internal inspection of power generation machinery
Siemens Energy, Inc.
August 03, 2017 - N°20170219814

Internal components of power generation machinery, such as gas turbine engines, are inspected with a spherical, optical-camera inspection system, mounted within a camera housing on a distal end of a compact diameter, single-axis inspection scope. The inspection scope includes nested, non-rotatable telescoping tubes, which define an extension axis. Circumscribing, telescoping tubes have anti-rotation collars, which are in sliding engagement with ...
Sealing system for optical sensors in gas turbine engines
Siemens Aktiengesellschaft
August 03, 2017 - N°20170219424

A sealing system (20) for an optical sensor of a turbine engine that diverts and exhaust seal leakage away from the seal (22, 24) to prevent ingestion of humid air through the seal (22, 24) is disclosed. The sealing system (20) may include inner and outer optical housings (26, 28) with first and second seals (22, 24) positioned there between separating inner and outer optical housings (26, 28) radially. The sealing system (20) ...
Compressor rotor with anti-vortex fins
Pratt & Whitney Canada Corp.
August 03, 2017 - N°20170218980

A compressor rotor of a gas turbine engine includes a rotor body having a face adapted to face an adjacent rotor. The rotor body extends radially between an outer peripheral rim surface and an inner rim surface. The inner rim surface defines a bore of the rotor body. A plurality of blades extends radially from the outer peripheral rim surface. ...
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