公开(公告)号：US20190242265A1

公开(公告)日：2019-08-08

申请号：US16384488

申请日：2019-04-15

Applicant: United Technologies Corporation

Inventor： Paul M. Lutjen ,  Jeremy Drake ,  Timothy M. Davis

IPC: F01D11/00 ,  F16J15/08 ,  F16J15/10 ,  F16J15/02 ,  F16J15/34

CPC classification number: F01D11/005 ,  F01D11/003 ,  F05D2220/32 ,  F05D2240/55 ,  F16J15/022 ,  F16J15/0806 ,  F16J15/0887 ,  F16J15/102 ,  F16J15/104 ,  F16J15/3452 ,  Y02T50/672

Abstract: The present disclosure relates generally to a sliding seal between two components. The sliding seal includes a first seal section and an uncoupled second seal section which allows the first and second seal sections to move relative to one another during relative movement between the two components. One or more spring tabs extend from the second seal section and bias the first and second seal sections away from one another.

公开(公告)号：US20190242263A1

公开(公告)日：2019-08-08

申请号：US16386578

申请日：2019-04-17

Applicant: General Electric Company

Inventor： David Alan Frey ,  Samir Armando Salamah ,  Charles William Craig, III

IPC: F01D9/04 ,  F01D5/18

CPC classification number: F01D9/041 ,  F01D5/187 ,  F05D2230/50 ,  F05D2260/20 ,  F05D2260/208 ,  F05D2300/6033 ,  Y02T50/672 ,  Y02T50/673 ,  Y02T50/676

Abstract: Ceramic matrix composite (CMC) airfoils and methods for forming CMC airfoils are provided. In one embodiment, an airfoil is provided that includes opposite pressure and suction sides extending radially along a span and opposite leading and trailing edges extending radially along the span. The leading edge defines a forward end of the airfoil, and the trailing edge defines an aft end of the airfoil. A trailing edge portion is defined adjacent the trailing edge at the aft end, and a pocket is defined in and extends within the trailing edge portion. A heat pipe is received in the pocket. A method for forming an airfoil is provided that includes laying up a CMC material to form an airfoil preform assembly; processing the airfoil preform assembly; defining a pocket in a trailing edge portion of the airfoil; and inserting a heat pipe into the pocket.

公开(公告)号：US20190195132A1

公开(公告)日：2019-06-27

申请号：US16328743

申请日：2017-08-28

Applicant: Unison Industries, LLC

Inventor： Gordon Tajiri ,  Michael Thomas Kenworthy ,  Yanzhe Yang ,  Dattu GV Jonnalagadda ,  Elizabeth Diane Turner

IPC: F02C7/18 ,  F28D1/02 ,  F28F7/02 ,  F28F3/04

CPC classification number: F02C7/18 ,  F05D2260/213 ,  F05D2270/42 ,  F05D2300/505 ,  F28D1/0246 ,  F28D2021/0021 ,  F28D2021/0026 ,  F28F3/048 ,  F28F7/02 ,  F28F2255/02 ,  F28F2255/04 ,  F28F2280/10 ,  F28F2280/105 ,  Y02T50/672 ,  Y02T50/675

Abstract: A fan casing assembly, connection assembly and method for moving a fan casing cooler. The fan casing assembly for the turbine engine can include an annular fan casing with a peripheral wall having a flow path defined through the casing. A fan casing cooler can mount along the peripheral wall in order to confront a cooling fluid flow within the flow path in order to cool a fluid through the fan casing cooler.

公开(公告)号：US20190048744A1

公开(公告)日：2019-02-14

申请号：US16157388

申请日：2018-10-11

Applicant: United Technologies Corporation

Inventor： David J. Sander ,  Shelton O. Duelm

IPC: F01D25/26 ,  F01D25/24 ,  F01D25/16 ,  F02C7/20 ,  F01D9/04

CPC classification number: F01D25/26 ,  F01D9/041 ,  F01D25/162 ,  F01D25/246 ,  F02C7/20 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2230/642 ,  F05D2230/644 ,  F05D2240/12 ,  F05D2240/14 ,  Y02T50/672 ,  Y02T50/673

Abstract: A method of assembling an attachment structure of a gas turbine engine includes providing a frame that has a first annular case, an inner annular case spaced radially inwardly from the first annular case, and a plurality of vanes extending between the inner case and the first annular case, providing a second annular case that extends around the frame, the first annular case and the second annular case include a plurality of interlocks, each of the plurality of interlocks includes a first member mounted on one of the first annular case or the second annular case and a corresponding second member mounted on the other of the first annular case or the second annular case, and inserting the first member in the second member such that the plurality of interlocks restricts relative circumferential and axial movement between the first annular case and the second annular case.

公开(公告)号：US20180347463A1

公开(公告)日：2018-12-06

申请号：US16045957

申请日：2018-07-26

Applicant: United Technologies Corporation

Inventor： Thomas W. Ward ,  Scot A. Webb

IPC: F02C7/047 ,  F01D25/02

CPC classification number: F02C7/047 ,  F01D25/02 ,  F05D2300/5024 ,  Y02T50/672

Abstract: A de-icing system for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a forward assembly and a rear assembly adjacent to the forward assembly. One of the forward assembly and the rear assembly is rotatable relative to the other to generate an amount of air friction between said forward and rear assemblies. A method of de-icing a gas turbine engine is also disclosed.

公开(公告)号：US20180347367A1

公开(公告)日：2018-12-06

申请号：US16001176

申请日：2018-06-06

Applicant: United Technologies Corporation

Inventor： Scott D. Virkler ,  Daniel E. Kane

IPC: F01D5/08 ,  F01D5/14 ,  F01D5/18 ,  F01D5/30

CPC classification number: F01D5/08 ,  F01D5/081 ,  F01D5/147 ,  F01D5/187 ,  F01D5/3007 ,  F01D5/3092 ,  F05D2220/32 ,  F05D2240/24 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2260/202 ,  F05D2260/231 ,  F05D2260/941 ,  F05D2270/112 ,  Y02T50/672 ,  Y02T50/676

Abstract: A rotor assembly for a gas turbine engine includes a rotor disk. The rotor disk includes a heat barrier feature radially inward of a rotor blade and radially outward of a rotor disk.

公开(公告)号：US20180346388A1

公开(公告)日：2018-12-06

申请号：US16056060

申请日：2018-08-06

Applicant: HONEYWELL INTERNATIONAL INC.

Inventor： Reza Oboodi ,  Eric Passman ,  Bahram Jadidian

IPC: C04B41/52 ,  C04B41/89 ,  F01D5/28 ,  C04B41/00 ,  C04B35/565 ,  C04B35/80 ,  C04B41/45 ,  C04B41/50

CPC classification number: C04B41/52 ,  C04B41/009 ,  C04B41/89 ,  F01D5/282 ,  F01D5/284 ,  F01D5/288 ,  F05D2300/2261 ,  F05D2300/6033 ,  Y02T50/672 ,  Y10T428/24364 ,  Y10T428/24612 ,  Y10T428/249955 ,  Y10T428/24999 ,  Y10T428/26 ,  C04B35/565 ,  C04B35/806 ,  C04B41/4537 ,  C04B41/5024 ,  C04B41/4582 ,  C04B41/5032 ,  C04B41/522 ,  C04B41/5048 ,  C04B41/5042 ,  C04B41/50

Abstract: Methods for fabricating protective coating systems for gas turbine engine applications are provided. An exemplary method of applying a protective coating to a substrate includes the steps of providing a substrate formed of a ceramic matrix composite material, forming a first coating layer directly on to the substrate and comprising an oxygen barrier material, a compliance material, or a bonding material and forming a second coating layer directly on to the first coating layer and comprising a thermal barrier material. The method optionally includes forming a third coating layer partially directly on to the second coating layer and partially within at least some of the plurality of pores of the second coating layer.

公开(公告)号：US20180328372A1

公开(公告)日：2018-11-15

申请号：US15709567

申请日：2017-09-20

Applicant: United Technologies Corporation

Inventor： Edward J. Gallagher ,  Byron R. Monzon ,  Shari L. Bugaj

IPC: F04D29/02 ,  F02K3/06 ,  F04D29/56 ,  F02C3/06

CPC classification number: F04D29/023 ,  F01D5/147 ,  F01D5/282 ,  F01D15/12 ,  F02C3/06 ,  F02C7/36 ,  F02K1/06 ,  F02K3/06 ,  F04D29/053 ,  F04D29/325 ,  F04D29/388 ,  F04D29/526 ,  F04D29/563 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2220/327 ,  F05D2220/36 ,  F05D2260/4031 ,  F05D2300/603 ,  Y02T50/672

Abstract: A gas turbine engine includes a gear assembly and a bypass flow passage that has an inlet. A fan is arranged within the bypass flow passage. A first turbine is coupled with a first shaft, which is coupled with the fan. A second turbine is coupled with a second shaft. The fan includes a hub and a row of fan blades that extend from the hub. The row includes 12 to 14 (N) of the fan blades, a solidity value (R) at tips of the fan blades that is greater than 0.85 and less than 1.1, and a ratio of N/R that is from 9 to 20.

公开(公告)号：US20180318873A1

公开(公告)日：2018-11-08

申请号：US16037917

申请日：2018-07-17

Applicant: United Technologies Corporation

Inventor： Ryan B. Noraas ,  Steven J. Bullied

IPC: B05D1/24 ,  F01D5/28 ,  B05D3/00 ,  B22C7/02 ,  B22C9/04 ,  C08J9/36

CPC classification number: B05D1/24 ,  B05D3/007 ,  B22C7/023 ,  B22C9/046 ,  C08J9/36 ,  F01D5/28 ,  F01D5/288 ,  F05D2220/36 ,  F05D2230/31 ,  F05D2240/303 ,  F05D2300/43 ,  F05D2300/603 ,  F05D2300/612 ,  Y02T50/672

Abstract: A foam for use in a lost-foam casting process utilized in the manufacture of a component for a gas turbine engine, the foam having a void fraction less than or equal to ninety five percent, is disclosed. The foam may include a first layer comprising polymer foam having an open-cell structure and a void fraction greater than ninety five percent. A second layer, comprising adhesive, may be adhered to the first layer. A third layer comprising particulate material may be adhered to the second layer.

公开(公告)号：US20180298773A1

公开(公告)日：2018-10-18

申请号：US15490478

申请日：2017-04-18

Applicant: Rolls-Royce North American Technologies, Inc.

Inventor： Daniel K. Vetters

IPC: F01D11/00 ,  F01D9/04 ,  F01D25/08 ,  F01D11/04

CPC classification number: F01D11/005 ,  F01D25/246 ,  F05D2230/642 ,  F05D2240/11 ,  F05D2300/6033 ,  Y02T50/672

Abstract: An assembly adapted for use in a gas turbine engine has a carrier component, a supported component, and a seal adapted to resist the flow of gasses between the supported component and the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for resisting gasses from passing over turbine blades included in the gas turbine engine.