公开(公告)号：US11421590B2

公开(公告)日：2022-08-23

申请号：US16656931

申请日：2019-10-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan ,  Arthur M. Salve, Jr.

IPC: F02C3/113 ,  F02C3/14 ,  F02C9/56 ,  F02K3/10 ,  F02C9/00

Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.

公开(公告)号：US11415044B2

公开(公告)日：2022-08-16

申请号：US16431271

申请日：2019-06-04

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Neil Terwilliger ,  Christopher J. Hanlon

IPC: F02C3/06 ,  F02C6/06 ,  F02C7/36 ,  F02C7/32

Abstract: An aircraft gas turbine engine system comprises first and second gas turbine engines. The first gas turbine engine has first and second spools. A first power linkage connects the second gas turbine engine to the first spool of the gas turbine engine, and a second power linkage connects the second gas turbine engine to the second spool of the first gas turbine engine.

公开(公告)号：US11408296B2

公开(公告)日：2022-08-09

申请号：US16272175

申请日：2019-02-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Mark E. Simonds ,  Steven J. Feigleson

IPC: F01D9/04 ,  F01D11/00 ,  F01D25/24 ,  F01D25/00

Abstract: A vane stage includes an arcuate platform defining an axial centerline axis having a pair of flanges that extend radially inward from the platform. The flanges are axially spaced from one another and from respective forward and aft ends of the platform. The vane stage includes a vane extending radially outward from the platform and a seal carrier mounted to the flanges of the platform. A method for constructing a vane stage includes sliding a seal carrier between flanges of an arcuate platform. Each flange includes at least a pair of through holes and interfaces with a respective axial side of the seal carrier. The method includes drilling through holes in each axial side of the seal carrier by using the through holes of each flange as guides.

公开(公告)号：US11384877B2

公开(公告)日：2022-07-12

申请号：US16257917

申请日：2019-01-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Edward Guevel

IPC: F16L23/08 ,  F02K1/80

Abstract: A retaining assembly may comprise a bracket assembly having a first end and a second end. The first end may be configured to mount to a clamping band. The retaining assembly may further comprise a retention component. The retention component may have a clevis coupled to the second end. The retaining assembly may be coupled to an otherwise loose external component on a gas turbine engine. The retaining assembly may keep the otherwise loose external component fixed to the gas turbine engine during maintenance operations and prevent the otherwise loose external component from being lost or misplaced.

公开(公告)号：US11384781B2

公开(公告)日：2022-07-12

申请号：US16589939

申请日：2019-10-01

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Seth Michael Glaser ,  James Evans ,  Michael C. Rhodes

IPC: F16B7/06 ,  F01D25/24

Abstract: A turnbuckle for adjustably locking a component of a gas turbine engine to an engine static structure is disclosed. In various embodiments, the turnbuckle includes an outer body having a first internal threading and an outer body witness hole, the outer body defining a first end configured for attachment to the component; an inner body having a first external threading, the inner body defining a second end configured for attachment to the engine static structure; and a coupling body having a second internal threading configured to threadedly engage the first external threading and a second external threading configured to engage the first internal threading, wherein the outer body witness hole extends through the outer body and is configured to detect a first short-threading of the second external threading within the first internal threading.

公开(公告)号：US11384654B2

公开(公告)日：2022-07-12

申请号：US16686540

申请日：2019-11-18

Applicant: United Technologies Corporation

Inventor： Winston Gregory Smiddy ,  San Quach ,  Matthew D. Parekh ,  Jeffrey T. Morton

IPC: F01D11/10 ,  F01D25/14

Abstract: A gas turbine engine includes one of a turbine section and a compressor section having multiple stages. At least one of the stages defines an outer diameter comprised of a plurality of circumferentially arranged blade outer air seals. Each blade outer air seal is spaced from each adjacent blade outer air seal in the plurality of circumferentially arranged blade outer air seals via a mateface gap. The mateface gap is oblique to a radius of the gas turbine engine, such that air entering the mateface gap is directed to an inner diameter surface of at least one of the blade outer air seals in the plurality of blade outer air seals.

公开(公告)号：US11379629B2

公开(公告)日：2022-07-05

申请号：US16797323

申请日：2020-02-21

Applicant: United Technologies Corporation

Inventor： Peter Cocks ,  Wookyung Kim

IPC: G06F30/00 ,  G06F30/17 ,  G06N3/08 ,  G06F30/20 ,  G06F111/20

Abstract: A process for designing an internal turbine engine component including operating a test rig incorporating a physical morphing component having a first geometry and generating a data set of empirically determined component performance parameters corresponding to the first geometry. Providing the data set of empirically determined component performance parameters to a computational optimization system and automatically. Determining a geometry optimization of the morphing component. Altering the geometry of the morphing component to match the geometry optimization. Reiterating operating the test rig and providing the data set of empirically determined component performance parameters.

公开(公告)号：US11377967B2

公开(公告)日：2022-07-05

申请号：US16705451

申请日：2019-12-06

Applicant: United Technologies Corporation

Inventor： Vladimir Skidelsky ,  Carlos Calixtro ,  Matthew B. DeGostin ,  John E. Paul ,  Mohamed Hassan ,  Charles Thistle ,  Jeffrey Michael Jacques

IPC: F01D5/22 ,  F01D11/00 ,  F01D5/08 ,  F01D5/30

Abstract: A damper seal for a turbine blade of a gas turbine engine, the damper seal having: an upper portion; a first downwardly curved portion; and a second downwardly curved portion, the first downwardly curved portion and the second downwardly curved portion extend from opposing end regions of the upper portion, the upper portion having a length extending between the opposing end regions of the upper portion and a width transverse to the length, wherein the upper portion is curved along the entire width as it extends along the length.

公开(公告)号：US11377965B2

公开(公告)日：2022-07-05

申请号：US15450087

申请日：2017-03-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Shawn J. Gregg ,  Dominic J. Mongillo ,  Michael Leslie Clyde Papple ,  Russell J. Bergman ,  Mohammed Ennacer

IPC: F01D5/18 ,  F01D9/04 ,  F01D25/12 ,  F02C7/12 ,  F04D29/32 ,  F04D29/54 ,  F04D29/58

Abstract: A component for a gas turbine engine includes, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.

公开(公告)号：US11376661B2

公开(公告)日：2022-07-05

申请号：US16433727

申请日：2019-06-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Brian A. Fisher ,  David W. Morganson

IPC: B22F3/24 ,  B22F5/00 ,  B24C3/16 ,  B24C3/10 ,  B24C3/00 ,  B24C1/00 ,  B24C3/32 ,  B24C1/04 ,  B24B19/14 ,  B33Y40/20

Abstract: A cutting system for removing an excess material along a length of a channel constructed using an additive manufacturing process is disclosed. In various embodiments, the cutting system includes a cutting component having an abrasive surface configured to remove the excess material along a down-facing surface of the channel and a smooth surface configured for sliding contact with an up-facing surface of the channel; and a motive component configured to urge the cutting component through the channel.