United Technologies Corporation

Raytheon Technologies Corporation

Siemens Energy, Inc.

Pratt & Whitney

John E Wilber

Jorge I Farah

Jonathan Ariel Scott

Kevin Michael Light

Ryan Patrick Murphy

Kalpendu J Parekh

David T Feindel

Holly Teufel

Bernard J Reilly

Harshawardhan S Bhide

Jesse T Carmichael

David M M Griffiths

Rimal K Patel

Jason T Silverman

Eric Joseph Oberson

Craig Hart

Ryan H Quinn

Rimal Patel

Jeffrey M Palitsch

Matthew R King

Kirk S Hunte

Matthew Russo King

A mid-turbine frame (MTF') for a jet engine is disclosed and comprises a duct that extends between a high pressure jet engine turbine ('HPT') and a low pressure jet engine turbine ('LPT&#x201d;), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.

Clamping seal for jet engine mid-turbine frame

A gas turbine engine includes a rotor hub that extends along a longitudinal axis of the gas turbine engine and includes a radially outer surface that has a substantially axially extending projection and a substantially radially extending projection. A seal ring includes a body portion and at least one knife edge that extends outward from the body portion. A recess is in the body portion for accepting the axially extending portion of the rotor hub. A lock ring is in abutting contact with the seal ring and the radially extending projection on the rotor hub for securing the seal ring to the rotor hub.

Rotor hub seal

A mid-turbine frame (MTF') for a jet engine is disclosed and comprises a duct that extends between a high pressure turbine ('HPT') and a low pressure turbine ('LPT&#x201d;), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.

Vane for jet engine mid-turbine frame

A mid-turbine frame (MTF') for a jet engine is disclosed and comprises a duct that extends between a high pressure jet engine turbine ('HPT') and a low pressure jet engine turbine ('LPT'), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.

A mid-turbine frame ('MTF') for a jet engine is disclosed and comprises a duct that extends between a high pressure turbine ('HPT') and a low pressure turbine (&#x201c;LPT&#x201d;), the duct comprising a plurality of segments that together form an outer annular structure and an inner annular structure, the inner annular structure situated radially inward of the outer annular structure, and/or a plurality of vanes that extend radially outward from the inner annular structure toward the outer annular structure, each vane comprising a channel. Each segment may be coupled to an adjacent segment by a seal.

Impingement structure for jet engine mid-turbine frame

An airfoil for a gas turbine engine and method of manufacture of the airfoil are disclosed. The airfoil may comprise a first side extending axially from a leading edge to a trailing edge and extending radially from a base to a tip, a second side opposite to the first side, a pocket disposed in the first side, a filler disposed in the pocket, and a preloaded spring disposed within the filler.

Fan blade damping device

Seal for jet engine mid-turbine frame

A gas turbine engine includes a rotor hub which includes a substantially axially extending projection and a substantially radially extending projection. A seal ring includes a body portion and at least one knife edge that extends outward from the body portion. A recess is in the body portion for accepting the axially extending portion of the rotor hub. The seal ring includes at least one cooling passage that extends through the seal ring. A lock ring is in abutting contact with the seal ring and the radially extending projection on the rotor hub for securing the seal ring to the rotor hub.

A turbine engine assembly and methods involving a turbine engine assembly are provided. In one method, the turbine engine assembly is received. The turbine engine assembly includes an annular stator vane structure disposed at a first orientation. The stator vane structure is reconfigured with the turbine engine assembly to be disposed at a second orientation.

Reconfiguring a stator vane structure of a turbine engine

A bladed rotor and a hub rotor for a gas turbine are provided. A bladed rotor may comprise a rotor interface comprising a radially inward surface, wherein the rotor interface comprises a constant diameter zone; and a reduced stress zone located adjacent to and aft of the constant diameter zone. A hub rotor may comprise a hub interface comprising a radially outward surface, wherein the hub interface comprises, a constant diameter zone, and a reduced stress zone located adjacent to and aft of the constant diameter zone.

Reduced stress rotor interface

An airfoil for a gas turbine engine is disclosed. The airfoil may include a leading edge, a sheath on the leading edge; and a grounding element connected to the sheath. The grounding element may have a radially extending tab, and may be configured for connection to a component of the gas turbine engine to form a ground path from the sheath to the component.

Fan blade grounding tab

A foil assembly for a gas powered turbine includes a plurality of floating wall sectors arranged circumferentially about an axis defined by a flowpath. Each of the floating wall sectors includes a first flowpath strut component, a second flowpath strut component, a floating wall panel connected to the first flowpath strut component by a first clamp seal at a first axial joint and connected to the second flowpath strut component by a second clamp seal at a second axial joint, and a plurality of leading edge structures fore of the plurality of floating wall sectors. Each of the leading edge structures is configured to define a foil profile in conjunction with a first flowpath strut component of a first floating wall sector and an adjacent flowpath strut component of a second floating wall sector.

Floating panel for a gas powered turbine

A seal ring for use between an integrally bladed rotor and a hub rotor of a compressor section of a gas turbine engine includes an arm configured to be positioned between the integrally bladed rotor and the hub rotor, such that the seal ring is removably coupled to the integrally bladed rotor and the hub rotor in response to a compressive force applied to the arm by the integrally bladed rotor and the hub rotor. The seal ring also includes a first blade coupled to the arm and configured to form a seal between a first volume and a second volume.

Clamped HPC seal ring

A mid-turbine frame for a gas turbine engine ducts gases between a high pressure turbine and a low pressure turbine. The mid-turbine frame may include an outer flowpath ring, an inner flowpath ring, and a plurality of vanes extending therebetween. The outer flowpath ring comprises a unitary structure, while the inner flowpath ring and the plurality of vanes comprises a plurality of segments.

Mid-turbine frame and gas turbine engine including same

Broken remnants of turbine engine rotor thru-bolt/nut interfaces are enveloped in a housing that is coupled to the rotor, so that the remnant does not migrate to other portions of the engine. In exemplary embodiments the housing directly mates with and engages the thru-bolt stud male threaded portion that projects outwardly from the nut, such as by a female threaded sleeve that is engaged with the male threads. The sleeve is in turn coupled to and/or supported by the rest of the housing. Some housing embodiments surround one or more of the threaded stud/nut interfaces. Housing embodiments of the invention are installed in situ without removing the rotor structure from the engine.

Growing community of inventors

East Hampton, CT, United States of America

John E Wilber