公开(公告)号：US12234735B1

公开(公告)日：2025-02-25

申请号：US18428397

申请日：2024-01-31

Applicant: RTX CORPORATION

Inventor： Joseph Micucci ,  Daniel S. Rogers ,  Morely S. Sherman

IPC: F01D11/12

Abstract: A gas turbine engine includes a turbine section that has a seal system disposed in interfaces between adjacent blade outer air seals. The seal system includes a first seal and at least one second seal that partially overlaps the first seal, the at least one second seal is configured to bias the first seal into a sealing position.

公开(公告)号：US12203375B2

公开(公告)日：2025-01-21

申请号：US17871063

申请日：2022-07-22

Applicant: General Electric Company

Inventor： Narendra Anand Hardikar ,  Deepak Trivedi ,  Ravindra Shankar Ganiger ,  Scott Alan Schimmels ,  Kevin Richard Graziano

IPC: F01D11/02 ,  F01D11/12

Abstract: A seal assembly at a rotor-stator interface includes at least one non-contacting seal interface and at least one rub detection feature. The rub detection feature(s) is configured to generate a signal upon the rotor and the stator making contact at the rotor-stator interface and causing wear above a certain threshold at the rotor-stator interface. The seal assembly also includes at least one sensor arranged at the rotor-stator interface. The sensor is configured to sense the signal. The seal assembly further includes a controller communicatively coupled with the sensor(s). The controller is configured to receive the signal and estimate at least one of an amount and a location of the wear at the rotor-stator interface based on the signal.

公开(公告)号：US12196099B2

公开(公告)日：2025-01-14

申请号：US18398597

申请日：2023-12-28

Applicant: General Electric Company

Inventor： Jan Christopher Schilling ,  Andrew John Breslin ,  Bryce Loring Heitman

IPC: F01D25/24 ,  F01D9/04 ,  F01D11/12

Abstract: A shroud hanger assembly is provided for hangers and shrouds defining dimensionally incompatible components such as those which are press or frictionally fit to engage one another. The shroud hanger assembly includes a multi-piece hanger and a shroud that is pinned to the hanger assembly by at least one axially extending pin and which locates the shroud relative to the hanger to control motion in one or both of circumferential (tangential) and radial directions relative to the engine.

公开(公告)号：US12116904B2

公开(公告)日：2024-10-15

申请号：US17597982

申请日：2020-07-29

Applicant: SAFRAN HELICOPTER ENGINES

Inventor： Bertrand Guillaume Robin Pellaton ,  Lucas Benassis

IPC: F01D5/22 ,  F01D11/00 ,  F01D11/10 ,  F01D11/12

CPC classification number: F01D5/22 ,  F01D5/225 ,  F01D11/001 ,  F01D11/10 ,  F01D11/122 ,  F01D11/127 ,  F05D2220/323 ,  F05D2240/55 ,  F05D2250/283

Abstract: Disclosed is a movable vane (1) for a wheel (2) of an aircraft turbine engine, the vane (1) comprising a blade (4) delimited by an outer heel (8) comprising a first seal (14), the vane (1) comprising an internal circuit (16) suitable for receiving a first minor gas flow (f1), this circuit (16) comprising a supply cavity (17) opening at the root (9) via at least one inlet opening (18), characterised in that the circuit (16) comprises at least two channels (19) connected with the supply cavity (17) and each opening on an outer surface of the first seal (14) via a discharge opening such that a gas jet (J) of the first minor gas flow (f1) is capable of being discharged from each discharge opening, each channel (19) being oriented such that the corresponding gas jet (J) is capable of being projected towards a second minor gas flow (f2) escaping between the heel (8) and a directly adjacent member (22).

公开(公告)号：US12104699B2

公开(公告)日：2024-10-01

申请号：US17715781

申请日：2022-04-07

Applicant: Blue Origin, LLC

Inventor： Ryan Linderman ,  Jacob Mills

IPC: F16J15/34 ,  F02K9/48 ,  F01D11/00 ,  F01D11/12

CPC classification number: F16J15/3432 ,  F02K9/48 ,  F16J15/34 ,  F16J15/3408 ,  F16J15/3412 ,  F16J15/346 ,  F01D11/003 ,  F01D11/122 ,  F05D2220/30 ,  F05D2240/55

Abstract: A representative seal system (such as a seal system for a turbopump of a rocket engine) automatically adjusts a balance ratio of a seal. The system can include a ring element encircling an axis. A front side of the ring element contacts a revolving surface to form a seal with the revolving surface. The front side can include a stepped surface having two or more steps. Each step includes a sealing surface configured to contact the revolving surface to form a sealing area that is different from a sealing area of each other sealing surface. Each step is positioned and configured to wear away during operation of the machine to expose an underlying surface to the revolving surface, to change the sealing area and the balance ratio of the seal. A representative method of operating a turbomachinery system includes changing the balance ratio of a seal while rotating a rotor.

公开(公告)号：US20240318574A1

公开(公告)日：2024-09-26

申请号：US18736906

申请日：2024-06-07

Applicant: LORD Corporation

Inventor： Russell E. Altieri ,  Victor Zaccardo ,  Paul R. Black ,  Douglas Swanson ,  Daniel E. Kakaley

IPC: F01D21/00 ,  F01D11/12 ,  G01B7/14

CPC classification number: F01D21/003 ,  F01D11/122 ,  G01B7/14 ,  F05D2270/303 ,  F05D2270/304 ,  F05D2270/305 ,  F05D2270/802 ,  F05D2270/807 ,  F05D2270/821

Abstract: Systems and methods for measuring a clearance between a rotating machine component and a sensor unit are disclosed. In some aspects, a system includes a sensor unit oriented to detect the rotating machine component as the rotating machine component rotates past the sensor unit, the sensor unit including at least a first sensing element and a second sensing element spaced apart from the first sensing element. The system includes a sensor processing unit in electrical communication with the sensor unit. The sensor processing unit is configured for receiving a first waveform from the first sensing element; receiving a second waveform from the second sensing element; and determining, based on a comparison between the first waveform and the second waveform, a distance between the blade tip and the sensor unit.

公开(公告)号：US12084988B2

公开(公告)日：2024-09-10

申请号：US17593226

申请日：2020-03-06

Applicant: NUOVO PIGNONE TECNOLOGIE—S.r.l.

Inventor： Michelangelo Bellacci ,  Gianfranco Maffulli ,  Lorenzo Cosi ,  Nicola Ciarla

IPC: F01D5/28 ,  C10G11/18 ,  C10G75/00 ,  F01D5/20 ,  F01D11/12

CPC classification number: F01D5/288 ,  C10G11/18 ,  C10G75/00 ,  F01D5/20 ,  F01D11/122 ,  F05D2220/62 ,  F05D2230/90 ,  F05D2240/307 ,  F05D2300/6111

Abstract: A blade for fluid catalytic cracking (FCC) flue hot gas expander with a layer of hard abrasive material localized on the blade tip that contributes to reducing the accumulation of FCC catalyst residuals in the expander.

公开(公告)号：US12055047B2

公开(公告)日：2024-08-06

申请号：US17781219

申请日：2020-12-01

Applicant: MTU Aero Engines AG

Inventor： Alexander Klötzer

IPC: F01D11/12

CPC classification number: F01D11/127 ,  F05D2220/323 ,  F05D2240/55 ,  F05D2250/283

Abstract: The invention relates to a seal carrier for a turbomachine, in particular a gas turbine, having a carrier base and at least one seal body, wherein the at least one seal body is connected to the carrier base, and wherein the at least one seal body is formed by a plurality of cavities arranged next to one another, in particular uniformly, in the peripheral direction and in the axial direction, wherein the cavities extend out from the carrier base in the radial direction and are delimited by a cavity wall. According to the invention, the seal body has a plurality of damping portions which are designed to locally damp or disrupt the flow of force in the seal body, wherein the carrier base is continuous in the region of the damping portions.

公开(公告)号：US12031444B2

公开(公告)日：2024-07-09

申请号：US17995818

申请日：2021-04-01

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Teddy Frederic Gilbert Chantrait ,  Antoine Robert Alain Brunet ,  Mael Thevenot ,  Gilles Jean-Luc Dessein ,  Jean-Yves Fernand Paris ,  Vincent Gilbert Alex Wagner

IPC: F01D11/12

CPC classification number: F01D11/122 ,  F05D2240/55

Abstract: A sealing assembly (1) for a turbine engine comprising a first element (2) and a second element (3), the first and second elements (2, 3) being concentric and in relative rotational movement with respect to each other about an axis of rotation (X), the sealing assembly (1) comprising at least one first wiper (4a) and an abradable member (5), the first wiper (4a) being annular in shape and carried by the first element (2), the first wiper (4a) extending radially towards the abradable member (5) and continuously around the axis of rotation (X), the abradable member (5) being annular in shape and carried by the second element (3), the abradable member (5) extending tangentially opposite the first wiper (4a), the first wiper (4a) comprising primary angular portions (11), each extending tangentially along a primary angular sector (11′), the primary angular portions (11) each having, in cross-section, a first constant profile, characterised in that the first wiper (4a) comprises secondary angular portions (13) each extending tangentially along a secondary angular sector (13′), the secondary angular portions (13) each having, in cross-section, a second profile different from the first profile, the number of secondary angular portions (13) being equal to the number of primary angular portions (11), the secondary angular portions (13) being interposed between the primary angular portions (11).

公开(公告)号：US20240209738A1

公开(公告)日：2024-06-27

申请号：US18418909

申请日：2024-01-22

Applicant: General Electric Company

Inventor： Daniel Endecott Osgood ,  Zachary Daniel Webster ,  Gregory Terrence Garay ,  Kevin Robert Feldmann

IPC: F01D5/18 ,  F01D1/12 ,  F01D5/14 ,  F01D5/28 ,  F01D11/12 ,  F01D11/14

CPC classification number: F01D5/186 ,  F01D1/12 ,  F01D5/147 ,  F01D5/284 ,  F01D11/12 ,  F01D11/122 ,  F01D11/14 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2230/311 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2300/514

Abstract: A component for a turbine engine includes a body with an exterior surface abutting a combustion flowpath for a combustion gas flow through the turbine engine, a cooling passage defined within the body, and a trench on the exterior surface. The trench includes a plurality of outlets, and a plurality of cooling holes extending from the cooling passage to the corresponding plurality of outlets.