公开(公告)号：US11236619B2

公开(公告)日：2022-02-01

申请号：US16404774

申请日：2019-05-07

Applicant: United Technologies Corporation

Inventor： Daniel A. Bales ,  Michael DuPont ,  Eric W. Malmborg

IPC: B23K1/00 ,  F01D5/00 ,  F01D5/18 ,  B23K101/00

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil body extending between leading and trailing edges in a chordwise direction and extending from a root section in a spanwise direction, and the airfoil body defining pressure and suction sides separated in a thickness direction. The airfoil body defines a recessed region extending inwardly from at least one of the pressure and suction sides, and the airfoil body includes one or more ribs that define a plurality of pockets within a perimeter of the recessed region. A plurality of cover skins is welded to the airfoil body along the one or more ribs to enclose respective ones of the plurality of pockets. The plurality of cover skins formed from a common cover having a perimeter that is dimensioned to mate with the perimeter of the recess. A method of forming a gas turbine engine component is also disclosed.

公开(公告)号：US11230975B2

公开(公告)日：2022-01-25

申请号：US16358760

申请日：2019-03-20

Applicant: United Technologies Corporation

Inventor： Nigel David Sawyers-Abbott ,  Federico Papa

IPC: F02C7/25 ,  A62C3/08 ,  F02C9/18 ,  F02C9/34 ,  F02K3/04 ,  B64D45/00

Abstract: A gas turbine engine includes an engine core having a compressor, a combustor fluidly connected to the compressor, and a turbine fluidly connected to the combustor. A core nacelle is disposed radially outward of the engine core. A cavity is disposed between an inner surface of the core nacelle and an outer surface of the engine core. The cavity includes a vent disposed at an aft end. The vent includes at least one flap configured to be maintained in an unrestricted position and in a restricted position. An actuator is configured to control the position of the at least one flap.

公开(公告)号：US11220924B2

公开(公告)日：2022-01-11

申请号：US16583618

申请日：2019-09-26

Applicant: United Technologies Corporation

Inventor： Robin H. Fernandez

IPC: F01D11/00 ,  F01D11/16 ,  F02C7/28 ,  F01D11/08

Abstract: A seal assembly for a gas turbine engine includes a seal including a main body extending circumferentially between opposed mate faces. The main body has a sealing portion and an engagement portion extending outwardly from sealing portion along at least one of the mate faces. The main body has a core including one or more core plies arranged to establish an internal cavity. An overwrap has one or more overwrap plies arranged to follow a perimeter of the one or more core plies to establish the engagement portion and the sealing portion. A platform insert extends between portions of the core and the overwrap to establish the sealing portion. A method of fabricating a seal for a gas turbine engine is also disclosed.

公开(公告)号：US11215054B2

公开(公告)日：2022-01-04

申请号：US16668820

申请日：2019-10-30

Applicant: United Technologies Corporation

Inventor： Nicholas D. Stilin

IPC: F02C3/04 ,  F01D5/02

Abstract: An airfoil according to an example of the present disclosure includes, among other things, an airfoil section extending between a leading edge and a trailing edge in a chordwise direction and extending between a tip portion and a root section in a spanwise direction. The airfoil section defines pressure and suction sides separated in a thickness direction, and includes a sheath having first and second sheath portions extending along an airfoil body of the airfoil section. The first sheath portion includes a first interface portion, and the second sheath portion includes a second interface portion that cooperates with the first interface portion to establish a joint having a circuitous profile along an edge of the airfoil body. A method of assembly for an airfoil is also disclosed.

公开(公告)号：US11208950B2

公开(公告)日：2021-12-28

申请号：US14259180

申请日：2014-04-23

Applicant: United Technologies Corporation

Inventor： Eric J. Wehmeier

IPC: F02C9/20 ,  F02C3/13 ,  F02C7/262 ,  F02K3/06 ,  F02K1/12 ,  F02K3/075 ,  F01D19/00

Abstract: A gas turbine engine includes a compressor section, the compressor section including a variable inlet guide vane which is movable between distinct angles to control the airflow approaching the compressor section. A control is programmed to position the vane at startup of the engine to direct airflow across the compressor section. The engine includes a fan for delivering bypass air into a bypass duct positioned outwardly of a core engine including the compressor section. The position of the vane is configured to direct airflow across the compressor section while an aircraft associated with the gas turbine engine is in the air, and to increase a windmilling speed of the compressor section and the turbine rotors. A method and variable inlet vane are also disclosed.

公开(公告)号：US11203936B2

公开(公告)日：2021-12-21

申请号：US16251537

申请日：2019-01-18

Applicant: United Technologies Corporation

Inventor： Eric W. Malmborg ,  Larry Foster

IPC: F01D5/14 ,  F16B5/06 ,  F16B13/02 ,  F16B13/00

Abstract: An airfoil includes a body that has rib nodes that each define a node cavity therein. A cover panel is carried on the body over the rib nodes. The cover panel includes tabs that project into the node cavities. Plugs are disposed in the node cavities and pinch the tabs against the node cavities to lock the cover panel on the body.

公开(公告)号：US11193384B2

公开(公告)日：2021-12-07

申请号：US16574589

申请日：2019-09-18

Applicant: United Technologies Corporation

Inventor： Pantcho P. Stoyanov ,  Mark B. Gossner

IPC: F01D11/00 ,  C01B32/20

Abstract: A method for preparing a seal assembly for a gas turbine engine, comprising a seal comprising a carbon material; and a seal seat positioned for rotation relative to the seal, wherein the method comprises the steps of: pre-filming a sealing surface of the seal seat with a carbon-based tribofilm; and assembling the seal seat relative to the seal in a gas turbine engine.

公开(公告)号：US11187096B2

公开(公告)日：2021-11-30

申请号：US16677262

申请日：2019-11-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Bryan H. Farrar ,  Howard J. Liles

IPC: F01D9/04 ,  F01D11/00 ,  F01D25/12

Abstract: A gas turbine engine includes a plurality of airfoil vanes situated in a circumferential row about an engine central axis. Each of the plurality of airfoil vanes include a first platform, and a second platform, and an airfoil section therebetween. A face of the first platform includes a trailing edge recess and a leading edge recess. The trailing edge recess and leading edge recesses of adjacent ones of the first platforms together define a slot. A sealing element situated in each slot. The sealing element has a geometry that tracks the geometry of the slot such that the seal is trapped in the slot by a form-fit relationship in circumferential and axial dimensions by a form-fit relationship between the sealing element and the slot. A method of sealing a plurality of airfoil vanes is also disclosed.

公开(公告)号：US11181074B2

公开(公告)日：2021-11-23

申请号：US16422181

申请日：2019-05-24

Applicant: United Technologies Corporation

Inventor： Oliver V. Atassi ,  Oleg Petrenko

IPC: F02K1/82 ,  F02K3/06 ,  F02C3/04 ,  F02K1/06 ,  F02K1/09 ,  F02C7/36 ,  F02K1/15

Abstract: A gas turbine engine includes a core engine that has at least a compressor section, a combustor section and a turbine section disposed along a central axis. A fan is coupled to be driven by the turbine section. A fan nozzle is aft of the fan and defines an exit area. The fan nozzle has a body with an airfoil cross-section geometry. The body includes a wall that has a controlled mechanical property distribution that varies in material macro- or micro-structure by location on the wall in accordance with a desired flutter characteristic at the location.

公开(公告)号：US11181004B2

公开(公告)日：2021-11-23

申请号：US16785204

申请日：2020-02-07

Applicant: United Technologies Corporation

Inventor： Amy M. Sunnarborg ,  Brendan J. Dugan

IPC: F01D11/00 ,  F16J15/02 ,  F16J15/08 ,  F16J15/10

Abstract: A pass through passage assembly of a gas turbine engine includes a compartment wall located between a first compartment and a second compartment, and a wall opening in the compartment wall connecting the first compartment and the second compartment, the wall opening having a central axis. A passage insert extends from the first compartment to the second compartment. A seal plate is positioned at the second compartment and extends about the central axis such that the compartment wall is located between an insert flange and the seal plate. A backing plate is positioned and retained between seal plate and the compartment wall, with the seal plate, the backing plate, the compartment wall, and the passage insert defining a seal cavity therebetween. A rope seal is located in the seal cavity and is retained in the seal cavity by the backing plate, the seal plate and the passage insert.