公开(公告)号：US20240352871A1

公开(公告)日：2024-10-24

申请号：US18761607

申请日：2024-07-02

Applicant: RTX Corporation

Inventor： David E. Bitter ,  William John Oldach ,  William C. Sheridan ,  Matthew Michael Massaro

IPC: F01D25/06 ,  F01D9/04

CPC classification number: F01D25/06 ,  F01D9/041 ,  F05D2220/323 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2260/96

Abstract: A hollow vane assembly including an open body including an interior; a cover brazed to the open body to form at least one flow passage; and at least one surface feature on an interior surface of the cover.

公开(公告)号：US20240110484A1

公开(公告)日：2024-04-04

申请号：US17937851

申请日：2022-10-04

Applicant: General Electric Company

Inventor： James Zhang ,  John McConnell Delvaux ,  Zachary John Snider

IPC: F01D5/16 ,  F01D9/04 ,  F01D25/06

CPC classification number: F01D5/16 ,  F01D9/041 ,  F01D25/06 ,  F05D2220/30 ,  F05D2230/60 ,  F05D2240/12 ,  F05D2240/30 ,  F05D2260/96

Abstract: A vibration damping system includes a vibration damping element for a turbomachine nozzle or blade. A body opening extends through the turbomachine nozzle or blade between the tip end and the base end thereof. A vibration damping element includes a volute spring vibration damping element configured to be installed within the body opening in the turbomachine nozzle or blade. The volute spring vibration damping element includes a spiral coil of a metal sheet strip with a surface of the metal sheet strip contacting itself in a direction of an axis of the coil. The body opening has an inner dimension, and the volute spring vibration damping element has an outer dimension sized to frictionally engage the inner dimension of the body opening to dampen vibration. In certain embodiments, the body opening and the volute spring vibration damping element each have a conical perspective shape.

公开(公告)号：US20240035384A1

公开(公告)日：2024-02-01

申请号：US17815372

申请日：2022-07-27

Applicant: General Electric Company

Inventor： Zachary John Snider ,  Brad Wilson VanTassel ,  Brian Denver Potter ,  John McConnell Delvaux

IPC: F01D25/04 ,  F01D25/06

CPC classification number: F01D25/04 ,  F01D25/06 ,  F05D2220/32 ,  F05D2260/96

Abstract: A vibration dampening system includes a vibration dampening element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration dampening element includes a plurality of stacked damper pins within the body opening. The damper pins include an outer body having an inner opening, a first end surface and an opposing second end surface; and an inner body nested and movable within the inner opening of the outer body. The end surfaces frictionally engage to dampen vibration. The inner body has a first central opening including a first portion configured to engage an elongated body therein and an outer surface configured to frictionally engage a portion of the inner opening of the outer body to dampen vibration.

公开(公告)号：US11865556B2

公开(公告)日：2024-01-09

申请号：US17614135

申请日：2020-05-28

Applicant: Ohio State Innovation Foundation

Inventor： Mohammad Arif Hossain ,  Jeffrey P. Bons ,  James W. Gregory ,  Ali Ameri

IPC: F01D25/06 ,  B05B1/08

CPC classification number: B05B1/08 ,  F01D25/06

Abstract: Various implementations include, an out-of-plane feedback-type fluidic oscillator. including a first portion, a second portion, a middle portion coupled between the first portion and the middle portion, and an axis of rotation. The middle portion includes a first side, a second side opposite and spaced apart from the first side, and a middle plane, an interaction chamber, a fluid supply inlet, an outlet nozzle, a first feedback a channel, and a second feedback channel. The first side is coupled to the first portion, and the second side is coupled to the second portion. The first side, the second side, and the middle plane extend circumferentially around the axis of rotation. The middle plane is disposed equally distanced from the first side and the second side. The fluid stream oscillates as it flows through the interaction chamber such that the fluid stream oscillates as the fluid stream exits the outlet nozzle.

公开(公告)号：US11828191B2

公开(公告)日：2023-11-28

申请号：US17614226

申请日：2020-05-27

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Philippe Gérard Edmond Joly ,  Romain Nicolas Lagarde ,  Jean-Marc Claude Perrollaz ,  Laurent Jablonski ,  François Jean Comin ,  Edouard Antoine Dominique Marie De Jaeghere ,  Charles Jean-Pierre Douguet

IPC: F01D5/16 ,  F01D5/10 ,  F01D5/22 ,  F01D5/26 ,  F01D25/06

CPC classification number: F01D5/16 ,  F01D5/10 ,  F01D5/22 ,  F01D5/26 ,  F01D25/06 ,  F05D2220/30 ,  F05D2240/30 ,  F05D2260/96

Abstract: A turbomachine assembly includes a casing, first and second rotors, and a damper. The first rotor includes a disk and blades and is movable in rotation relative to the casing. The second rotor is movable relative to the casing around a longitudinal axis. The damper damps a movement of the first rotor relative to the second rotor. The damper includes first to third parts. The first part bears on the first rotor in a first area extending over a first angular sector around the longitudinal axis and applies a first centrifugal force on the first rotor. The second part bears on the first rotor in a second area that is smaller than the first angular sector and extends over a second angular sector around the longitudinal axis. The third part bears on the second rotor and applies a second centrifugal force on the second rotor.

公开(公告)号：US20190112928A1

公开(公告)日：2019-04-18

申请号：US15787478

申请日：2017-10-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： PETER V. TOMEO ,  CARNEY R. ANDERSON

IPC: F01D5/02 ,  F04D29/66 ,  F04D29/32 ,  F01D5/30 ,  F04D29/34

CPC classification number: F01D5/027 ,  F01D5/10 ,  F01D5/16 ,  F01D5/26 ,  F01D5/3015 ,  F01D5/3023 ,  F01D5/326 ,  F01D9/041 ,  F01D11/006 ,  F01D25/04 ,  F01D25/06 ,  F04D29/321 ,  F04D29/325 ,  F04D29/34 ,  F04D29/662 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2260/30 ,  F05D2260/96

Abstract: A rotor disk assembly may include a rotor disk and a retention ring coupled to the rotor disk. Generally, the retention ring is tuned to adjust a modal frequency response of the rotor disk/rotor disk assembly. In various embodiments, dimensions of the retention ring vary circumferentially. In various embodiments, the retention ring includes an axially extending flange and a radially extending flange. A radial thickness of the axially extending flange may vary circumferentially and/or an axial thickness of the radially extending flange may vary circumferentially.

公开(公告)号：US20180258857A1

公开(公告)日：2018-09-13

申请号：US15452634

申请日：2017-03-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dilip Prasad ,  Bruce L. Morin

IPC: F02C7/045 ,  F01D25/06

CPC classification number: F02C7/045 ,  B64D2033/0206 ,  F01D25/06 ,  F02K1/827 ,  F02K3/06 ,  F05D2260/96 ,  F05D2260/963 ,  G10K11/172 ,  Y02T50/672

Abstract: Disclosed is a flutter damper including a first plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a first fan flutter mode, the first plurality of chambers in fluid communication with a flow surface, and a second plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a second fan flutter mode, the second plurality of chambers in fluid communication with the flow surface, and wherein the first plurality of chambers and second plurality of chambers are disposed in a grid pattern.

公开(公告)号：US10053997B2

公开(公告)日：2018-08-21

申请号：US14881962

申请日：2015-10-13

Applicant: ROLLS-ROYCE PLC

Inventor： Stephane Michel Marcel Baralon

IPC: F01D9/04 ,  F01D9/02 ,  F01D25/06 ,  F02K3/04 ,  F01D5/02 ,  F01D25/24

CPC classification number: F01D9/041 ,  F01D5/02 ,  F01D9/02 ,  F01D25/06 ,  F01D25/24 ,  F02K3/04 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2250/14 ,  F05D2250/71 ,  F05D2260/96

Abstract: A gas turbine engine comprising in axial flow series: a fan having a fan rotor; a series passages defined between adjacent outlet guide vanes for guiding flow from the fan; and a bifurcation. The gas turbine engine further comprises a substantially annular fluid passageway extending from the fan to the bifurcation, the outlet guide vanes being positioned within the passageway. The passageway includes a profiled region. The profiled region includes a first circumferential portion positioned adjacent a second circumferential portion, the first circumferential portion having a first average radial thickness and a second circumferential portion having a second average radial thickness, the first average radial thickness being smaller than the second average radial thickness, wherein the first circumferential portion is positioned in a region corresponding to a circumferential position of the bifurcation, and wherein the profiled region is at an axial position corresponding to the axial position of the outlet guide vanes and the first circumferential portion extends continuously over two or more of the passages.

公开(公告)号：US20180230820A1

公开(公告)日：2018-08-16

申请号：US15431950

申请日：2017-02-14

Applicant: General Electric Company

Inventor： William Scott Zemitis ,  Melbourne James Myers ,  Richard Ryan Pilson ,  Calvin Levy Sims

IPC: F01D5/22 ,  F01D25/06

CPC classification number: F01D5/24 ,  B21D53/78 ,  F01D5/143 ,  F01D5/16 ,  F01D5/22 ,  F01D5/26 ,  F01D5/3015 ,  F01D25/06 ,  F05D2240/80 ,  F05D2260/96

Abstract: A turbine blade includes an airfoil that extends radially between a root end and a tip end, a platform coupled to the root end, and a shank that extends radially inwardly from the platform. The shank includes a cover plate. The cover plate includes an outer surface, an opposite inner surface, and a contoured face that at least partially defines a damper pin slot. The contoured face extends from the outer surface to a first blend edge. The cover plate also includes a blended surface that extends from the first blend edge to a second blend edge. The second blend edge intersects with the inner surface.

公开(公告)号：US09938854B2

公开(公告)日：2018-04-10

申请号：US14712067

申请日：2015-05-14

Applicant: United Technologies Corporation

Inventor： Alex J. Simpson ,  Timothy Charles Nash

IPC: F01D25/06 ,  F01D9/04 ,  F01D5/14 ,  F01D5/16 ,  F01D5/22 ,  F01D5/26 ,  F01D5/10 ,  F01D1/02 ,  F01D5/02

CPC classification number: F01D25/06 ,  F01D1/02 ,  F01D5/02 ,  F01D5/10 ,  F01D5/141 ,  F01D5/143 ,  F01D5/145 ,  F01D5/16 ,  F01D5/22 ,  F01D5/26 ,  F01D9/04 ,  F01D9/041 ,  F01D9/047 ,  F05D2220/32 ,  F05D2260/96 ,  Y02T50/673

Abstract: A gas turbine engine includes an array of airfoils. Each airfoil includes a first circumferentially extreme position. The first circumferentially extreme positions of the airfoils are circumferentially spaced apart from one another a pitch. Each airfoil includes a second circumferentially extreme position circumferentially spaced from the first circumferentially extreme position in an angular spacing that is at least one half the pitch.