公开(公告)号：US11795821B1

公开(公告)日：2023-10-24

申请号：US17658461

申请日：2022-04-08

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Dikran Mangardich

IPC分类号： F01D5/04

CPC分类号： F01D5/048 ,  F05D2220/323 ,  F05D2250/294 ,  F05D2260/941

摘要： A rotor for an aircraft engine, has: a hub extending circumferentially about a central axis, the hub having a bore, a gaspath-facing surface located radially outwardly of the bore relative to the central axis, a first face extending from the bore to the gaspath-facing surface, and a second face opposite the first face and extending from the bore to the gaspath-facing surface; blades circumferentially distributed about the central axis, the blades protruding away from the gaspath-facing surface of the hub; and a crack mitigator located on the first face, the crack mitigator extending circumferentially relative to the central axis, the crack mitigator extending axially from a baseline surface of the first face.

公开(公告)号：US11772778B2

公开(公告)日：2023-10-03

申请号：US17766047

申请日：2020-10-02

申请人： SAFRAN AIRCRAFT ENGINES

发明人： Tewfik Boudebiza ,  Julien Michel Patrick Christian Austruy ,  Gilles Alain Marie Charier ,  Cedrik Djelassi

IPC分类号： B64C11/40 ,  B64C11/30 ,  F01D7/00

CPC分类号： B64C11/40 ,  B64C11/30 ,  F01D7/00 ,  F05D2220/30 ,  F05D2240/30 ,  F05D2260/941

摘要： The invention describes a system for controlling the cyclic setting of blades (1) of a turbine engine propeller, the blades (1) being arranged in a plane normal to the axis of rotation (r) of the propeller, the system comprising: —a plate assembly (40) that can be tilted relative to the normal plane (P), —an articulation system (50) articulating the plate assembly (40) relative to the blades (1) such that tilting the plate assembly (40) modifies the setting of the blades (1), —a force sensor (5) designed to measure a force applied in the normal plane (P) by an air flow at the inlet of the propeller blades (1), —a cylinder (60) suitable for tilting the plate assembly (40) in response to a force measured by the force sensor (5).

公开(公告)号：US20230304447A1

公开(公告)日：2023-09-28

申请号：US17703546

申请日：2022-03-24

申请人： General Electric Company

发明人： Constantinos Minas ,  William Morton

IPC分类号： F02C9/18

CPC分类号： F02C9/18 ,  F05D2220/323 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2270/303 ,  F05D2270/44 ,  F05D2270/80 ,  F05D2260/941 ,  F05D2270/332

摘要： A minimum creep life location (MCLL) on a blade for a turbine blade design is received. A temperature at the MCLL on the blade is monitored. When the temperature at the MCLL exceeds a predetermined threshold, a cooling air supply is adjusted to lower the temperature below the threshold during engine operation.

公开(公告)号：US11655713B2

公开(公告)日：2023-05-23

申请号：US17572283

申请日：2022-01-10

申请人： STRESSWAVE, INC.

发明人： Eric T Easterbrook

IPC分类号： G01N3/42 ,  B23P6/04 ,  F01D5/00 ,  G01B7/26 ,  G06F30/17

CPC分类号： F01D5/005 ,  B23P6/045 ,  G01B7/26 ,  G01N3/42 ,  G06F30/17 ,  F05D2230/232 ,  F05D2230/80 ,  F05D2260/821 ,  F05D2260/941

摘要： Repaired rotors are provided. The rotors are repaired by using an indenter apparatus for plastically straining original portions of the rotor and adjacent repair welds. The weld nugget, adjacent heat affected zones, and the adjacent parent-metal portions or new metal portions, are indented at a weld nugget and heat affected zone, to produce threshold levels of uniform plastic strain which meet or exceed plastic strain levels that provide, when the weld nugget and heat affected zone is heat treated, a recrystallized grain structure metallurgically comparable to the grain structure of the original parent-metal of the rotor. Repaired integrally bladed rotors for gas turbine engines, such as aircraft engines, are provided. Blades for gas turbine engines, including integrally bladed rotors, may be advantageously provided, having been manufactured or repaired as described.

公开(公告)号：US20190234219A1

公开(公告)日：2019-08-01

申请号：US16249079

申请日：2019-01-16

申请人： MTU Aero Engines AG

发明人： Martin PERNLEITNER ,  Klaus WITTIG ,  Lutz FRIEDRICH

IPC分类号： F01D5/20

CPC分类号： F01D5/20 ,  F01D5/147 ,  F01D5/225 ,  F05D2230/10 ,  F05D2230/21 ,  F05D2240/307 ,  F05D2250/75 ,  F05D2260/941

摘要： A shroud segment (100) for disposition on a blade of a turbomachine is provided, in particular a gas turbine, the shroud segment having a stiffening structure raised above a shroud segment surface (15), the stiffening structure including at least three interconnected ribs (3, 5, 7), and a first end portion of the ribs (3, 5, 7) being connected to an upstream sealing tip (11) of the shroud segment (100), and a second end portion of these ribs (3, 5, 7) being connected to a downstream sealing tip (13) of the shroud segment (100). The angles (W1, W2, W3) between the direction of the axis of rotation (a) of the blade and the longitudinal orientations (21, 23, 25) of the ribs (3, 5, 7), as viewed in the direction of flow (9) through the turbomachine, are between zero degrees and eighty degrees. The present invention also relates to a blade (200) of a turbomachine.

公开(公告)号：US20190010827A1

公开(公告)日：2019-01-10

申请号：US15994375

申请日：2018-05-31

申请人： General Electric Company

发明人： Javeed Iqbaluddin MOHAMMED ,  Pallab KARMAKAR ,  Bradly Aaron KIPPEL

IPC分类号： F01D25/26 ,  F01D25/32 ,  F01D11/00 ,  F01D25/00

CPC分类号： F01D25/26 ,  F01D11/005 ,  F01D25/005 ,  F01D25/32 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2230/642 ,  F05D2240/12 ,  F05D2240/55 ,  F05D2250/75 ,  F05D2260/30 ,  F05D2260/38 ,  F05D2260/941 ,  F05D2300/171 ,  F05D2300/501

摘要： An expansion joint for use between a turbine duct and a diffuser duct includes a first flange coupled to the turbine duct, a second flange coupled to the diffuser duct, and a flexible element positioned between and coupled to the first flange of the turbine duct and the second flange of the diffuser duct. The flexible element defines a trough for receiving a liquid therein. The trough includes a drain pipe configured to channel the liquid away from the trough.

公开(公告)号：US20180363913A1

公开(公告)日：2018-12-20

申请号：US15628257

申请日：2017-06-20

申请人： PRATT & WHITNEY CANADA CORP.

发明人： Guy BOUCHARD ,  Kenneth PARKMAN

IPC分类号： F23R3/48 ,  F23R3/50 ,  F23R3/26

CPC分类号： F23R3/48 ,  F01D1/023 ,  F01D11/02 ,  F01D25/125 ,  F01D25/183 ,  F01M2011/021 ,  F02C7/06 ,  F02C7/28 ,  F05D2220/32 ,  F05D2230/237 ,  F05D2260/941 ,  F16C33/1025 ,  F16C33/106 ,  F16C33/1085 ,  F16N39/00 ,  F16N2210/12 ,  F23R3/26 ,  F23R3/50 ,  F23R2900/00

摘要： A gas turbine engine comprises bearing(s). A structure supporting the bearing defines a bearing cavity surrounding the at least one bearing, an ambient chamber and an intermediate chamber having a portion between the bearing cavity and the ambient chamber, with at least one wall forming a passage from the bearing cavity to the ambient chamber and through the portion of the intermediate chamber. A tube is received in the passage and having a first end open to the bearing cavity and a second end open to the ambient chamber, the second end adapted to be connected to a conduit for fluid communication between the bearing cavity and the through the tube, wherein a portion of or near the first end of the tube is sealingly joined to the at least one wall, and the second end of the tube contacts the at least one wall and is free to move relative to the at least one wall.

公开(公告)号：US20180347367A1

公开(公告)日：2018-12-06

申请号：US16001176

申请日：2018-06-06

申请人： United Technologies Corporation

发明人： Scott D. Virkler ,  Daniel E. Kane

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

CPC分类号： 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

摘要： 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：US20180274549A1

公开(公告)日：2018-09-27

申请号：US15928193

申请日：2018-03-22

申请人： ebm-papst Mulfingen GmbH & Co. KG

发明人： Martin Baer ,  Erhard Gruber ,  Oliver Haaf ,  Alexander Konzal

IPC分类号： F04D29/34 ,  F04D29/32

CPC分类号： F04D29/34 ,  F04D19/005 ,  F04D29/325 ,  F04D29/388 ,  F04D29/646 ,  F05D2250/292 ,  F05D2260/941

摘要： A connecting element (1) interacting with a fan blade (50) to transfer torque of a drive to the fan blade (50). An attachment portion (2) connects the connecting element (1) with the fan blade. The attachment portion (2) forms an outer edge portion (4) adjoining the outer contour of the connecting element (1). The attachment portion (2) cross-sectional shape is designed to taper toward the outer edge in at least some portions.

公开(公告)号：US20180274449A1

公开(公告)日：2018-09-27

申请号：US15465224

申请日：2017-03-21

申请人： United Technologies Corporation

发明人： Christopher T. Anglin ,  Yuk-Kwan Brian Yuen

IPC分类号： F02C7/32 ,  F02C7/06 ,  F16H57/021 ,  F16H57/023 ,  F16H57/038

CPC分类号： F02C7/32 ,  F02C7/06 ,  F02C7/36 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/60 ,  F05D2260/941 ,  F16H57/021 ,  F16H57/023 ,  F16H57/038

摘要： A tower shaft support for a gearbox of a gas turbine engine includes a mounting ring, first and second gussets, and first and second tower shaft bearing mounts. Each gusset extends outward from and substantially normal to an outer circumference of the mounting ring. The first and second tower shaft bearing mounts are positioned between the first and second gussets.