公开(公告)号：US5593278A

公开(公告)日：1997-01-14

申请号：US568223

申请日：1983-12-30

Applicant: Gerard E. A. Jourdain ,  Jean-Paul Lagrange ,  Gerard M. F. Mandet ,  Jacques H. Mouchel ,  Jean-Philippe E. Richard ,  Marcel R. Soligny

Inventor： Gerard E. A. Jourdain ,  Jean-Paul Lagrange ,  Gerard M. F. Mandet ,  Jacques H. Mouchel ,  Jean-Philippe E. Richard ,  Marcel R. Soligny

IPC: F01D11/08 ,  F01D11/12 ,  F01D11/14 ,  F01D11/18 ,  F01D11/24 ,  F01D25/24

CPC classification number: F01D11/18 ,  F01D25/246 ,  Y02T50/67 ,  Y02T50/671

Abstract: The disclosed invention relates to a sealing device for the rotor blades of a gas turbine engine which permits real time adjustment to be made of the clearances between the rotor blade tips and the sealing structure. The sealing shroud around the turbine wheel is formed of sectors, each sector being attached to a monolithic short response time ring and a monolithic long response time ring. Ventilating air from upstream of the turbine wheel is directed onto the rings such that the sectors are caused to radially expand or contract in compliance with the expansion or contraction of the tips of the rotor blades during stabilized and transient engine operational modes. A small positive clearance between the sealing sectors and the blade tips is maintained throughout the range of the engine's operation.

Abstract translation: 所公开的本发明涉及一种用于燃气涡轮发动机的转子叶片的密封装置，其允许由转子叶片尖端和密封结构之间的间隙进行实时调节。 涡轮机轮周围的密封罩由扇形部分组成，每个扇形部分连接到单片短响应时间环和单片长响应时间环。 涡轮机叶轮上游的通风空气被引导到环上，使得在稳定和瞬态的发动机操作模式期间，这些扇区在转子叶片的尖端的膨胀或收缩下被引起径向膨胀或收缩。 在发动机运行的整个范围内，保持密封扇区和叶片尖端之间的小的正间隙。

公开(公告)号：US4818948A

公开(公告)日：1989-04-04

申请号：US893276

申请日：1986-08-05

Applicant: Kevin A. Dooley

Inventor： Kevin A. Dooley

IPC: F01D11/14 ,  G01B7/14 ,  G01D5/241 ,  G01R27/26 ,  H01G7/00

CPC classification number: F01D11/14 ,  G01B7/14 ,  G01D5/2417

Abstract: An elongated conductive casing is filled with a dielectric material and has an opening at one end. The dielectric material forms a surface across the opening, and a plate member is disposed on the surface to form the sensitive arm of the capacitive probe. Formed within the casing are four capacitors, including the sensitive arm, which form a capacitive probe.

Abstract translation: 细长的导电外壳填充有电介质材料，并在一端具有开口。 电介质材料形成穿过开口的表面，并且板构件设置在表面上以形成电容式探针的敏感臂。 在壳体内形成四个电容器，包括形成电容式探头的敏感臂。

公开(公告)号：US12234736B2

公开(公告)日：2025-02-25

申请号：US18209805

申请日：2023-06-14

Applicant: General Electric Company

Inventor： Taehong Kim ,  Marcia Boyle Johnson ,  Daniel E. Reisenauer

IPC: F01D11/14 ,  F01D11/10

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed to illustrate a clearance design process and strategy with CCA-ACC optimization for exhaust gas temperature (EGT) and performance improvement. In some examples, an apparatus includes a case surrounding at least part of a turbine engine, the at least part of the turbine engine including a turbine or a compressor. The apparatus further includes a first source to obtain external air; a second source to obtain cooled cooling air; a heat exchanger to control temperature of cooled cooling air; and a case cooler to provide active clearance control air to the case to control deflection of the case, wherein the active clearance control air is a combination of the external air and the cooled cooling air, the case cooler coupled to the heat exchanger using a first valve, the first valve triggered by a first control signal.

公开(公告)号：US20250035006A1

公开(公告)日：2025-01-30

申请号：US18716347

申请日：2023-01-13

Applicant: MITSUBISHI POWER, LTD.

Inventor： Tatsuro FURUSHO ,  Shin NISHIMOTO ,  Shintaro OKUMURA ,  Kenichi SAKASHITA ,  Masaya KAWANO ,  Kohei OZAKI ,  Azumi YOSHIDA

IPC: F01D11/14

Abstract: A sealing device including: a sealing member that is disposed between a rotating member of a rotating machine and a stationary member disposed on the outer side of the rotating member in the radial direction of the rotating member, and that creates a seal between the rotating member and the stationary member; and a biasing member that biases the sealing member toward the radially outer side. The sealing member has a base extending in the circumferential direction of the rotating member, a rib that extends in the circumferential direction and protrudes outward in the radial direction from the base, and a seal fin that extends in the circumferential direction and protrudes inward in the radial direction of the rotating member from the base. The rib has a cut-away part in which the biasing member is disposed between one end and the other end of the rib in the circumferential direction.

公开(公告)号：US20230417149A1

公开(公告)日：2023-12-28

申请号：US18463970

申请日：2023-09-08

Applicant: General Electric Company

Inventor： Ravindra Shankar Ganiger ,  Praveen Sharma ,  Jeffrey D. Carnes ,  Herbert Chidsey Roberts

IPC: F01D11/12 ,  F01D11/14

CPC classification number: F01D11/127 ,  F01D11/14 ,  F05D2240/11 ,  F05D2270/42 ,  F05D2260/38 ,  F05D2270/114 ,  F05D2250/183

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. A shroud assembly of a gas turbine engine includes: a first shroud arm having a first end and a second end, the first end to couple to an outer wall and the second end to couple to a first shroud pad, and a second shroud arm having a first end and a second end, the first end to couple to the outer wall and the second end to couple to a second shroud pad, at least one of the first shroud pad or the second shroud pad to move radially outward toward the outer wall in response to a rotor blade contacting the at least one of the first shroud pad or the second shroud pad.

公开(公告)号：US11560853B2

公开(公告)日：2023-01-24

申请号：US17466086

申请日：2021-09-03

Applicant: ROLLS-ROYCE PLC

Inventor： Craig W Bemment ,  Pascal Dunning

IPC: F02C9/28 ,  F01D11/14 ,  F01D13/00 ,  F01D25/24

Abstract: A gas turbine engine for an aircraft includes an engine core including a first, lower pressure, turbine, a first compressor, and a first core shaft connecting the first turbine to the first compressor; and a second, higher pressure, turbine, a second compressor, and a second core shaft connecting the second turbine to the second compressor, and a fan located upstream of the engine core and including a plurality of fan blades extending from a hub. A turbine to fan tip temperature change ratio of a low pressure turbine temperature change to a fan tip temperature rise is in the range from 1.46 to 2.0.

公开(公告)号：US11248485B1

公开(公告)日：2022-02-15

申请号：US16995467

申请日：2020-08-17

Applicant: General Electric Company

Inventor： Jonathan D. Baldiga ,  David W. Bogdan

IPC: F01D11/22 ,  F01D5/12 ,  F01D9/00 ,  F01D11/08 ,  F01D11/18 ,  F01D11/14

Abstract: Example apparatus, systems, and articles of manufacture to control deflection mismatch are disclosed herein. Further examples and combinations thereof include: A deflection limiter comprising an inner shroud segment to support a stator structure, the inner shroud segment including a first end face and a first outer upper portion, the first end face positioned radially inward and aft relative to the first outer upper portion, and an outer shroud segment to support the inner shroud segment, the outer shroud segment including a second end face and a second outer upper portion, the second end face positioned aft relative to the first end face and the second outer upper portion positioned aft relative to the first outer upper portion of the inner shroud segment, the second end face coupled to the first end face of the inner shroud segment and the second outer upper portion coupled to the first outer upper portion.

公开(公告)号：US11225908B2

公开(公告)日：2022-01-18

申请号：US16206262

申请日：2018-11-30

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Thomas Roger Jacques Angevin ,  Arnaud Baudran

IPC: F02C7/00 ,  F02C7/224 ,  F02C9/18 ,  F02C3/04 ,  F01D11/14 ,  F02C9/24 ,  F15B13/06 ,  F15B21/06 ,  F02C7/14

Abstract: A hydraulic and pneumatic control circuit for a turbojet, a main hydraulic line having an oil/fuel heat exchanger with a function of transferring heat from the oil flowing in an oil circuit of the turbojet to the fuel flowing in the main hydraulic line, the circuit having a first hydraulic line for feeding fuel to a combustion chamber of the turbojet, a second hydraulic line for feeding fuel to one or more actuators for controlling variable geometry equipment, each actuator being fed with fuel via an electrohydraulic servovalve, a pneumatic line for feeding air to a pneumatic control member for bleed valves of a compressor and a blade tip clearance control valve of a turbine of the turbojet, and a fuel/air heat exchanger positioned on the second hydraulic line upstream from the hydraulic servovalve and on the pneumatic line upstream from the pneumatic control member.

公开(公告)号：US11028718B2

公开(公告)日：2021-06-08

申请号：US16575971

申请日：2019-09-19

Applicant: General Electric Company

Inventor： Nathan Evan McCurdy Gibson ,  Darek Tomasz Zatorski

IPC: F01D11/10 ,  F01D5/03 ,  F01D11/06 ,  F01D5/22 ,  F01D25/24 ,  F01D1/26 ,  F02C3/067 ,  F01D11/14 ,  F01D11/16 ,  F02K3/072 ,  F01D11/02 ,  F04D29/54 ,  F04D27/00

Abstract: The present disclosure is directed to a gas turbine engine including a turbine rotor, a turbine frame at least partially surrounding the turbine rotor, and an outer diameter seal assembly. The turbine rotor includes an inner shroud, an outer shroud, and at least one connecting airfoil coupling the inner shroud and the outer shroud. The outer shroud includes a plurality of outer shroud airfoils extended inward along a radial direction. The outer diameter seal assembly includes a sliding portion disposed between the turbine frame and the outer shroud of the turbine rotor. The outer diameter seal assembly defines a secondary tooth at the outer shroud radially inward of a longitudinal face of the sliding portion, and a primary tooth defined axially adjacent to a radial face of the sliding portion.

公开(公告)号：US10774668B2

公开(公告)日：2020-09-15

申请号：US15709642

申请日：2017-09-20

Applicant: General Electric Company

Inventor： Richard Alan Wesling ,  Darek Tomasz Zatorski

IPC: F01D11/12 ,  F02C3/067 ,  F01D5/03 ,  F01D5/22 ,  F01D11/14 ,  F01D11/16 ,  F01D11/08 ,  F01D11/02 ,  F01D11/00 ,  F02K3/072

Abstract: The present disclosure is directed to a gas turbine engine including a turbine rotor assembly that includes a first turbine rotor and a second turbine rotor. The first turbine rotor includes an outer rotor and a plurality of outer rotors extended inwardly along a radial direction from the outer rotor. The second turbine rotor includes an inner rotor and a plurality of inner rotor airfoils extended outwardly along the radial direction from the inner rotor. The plurality of outer rotor airfoils and inner rotor airfoils are disposed in alternating arrangement along a longitudinal direction. One or more rotating seal interfaces are defined between the first turbine rotor and the second turbine rotor.