公开(公告)号：US12060806B1

公开(公告)日：2024-08-13

申请号：US18450755

申请日：2023-08-16

Applicant: RTX Corporation

Inventor： Michael G. McCaffrey

IPC: F01D25/32 ,  F01D5/08

CPC classification number: F01D25/32 ,  F01D5/081 ,  F05D2260/201 ,  F05D2260/607

Abstract: Tangential onboard injector assemblies include a TOBI and a TOBI blocker assembly arranged upstream of an inlet of the TOBI. The TOBI blocker assembly includes a first blocker plate upstream from the inlet and defining a blocker cavity between the first blocker plate and the TOBI. The first blocker plate includes a blocking portion and a filter portion to permit airflow therethrough. A second blocker plate is arranged within the blocker cavity to obstruct a flow of air containing particulate matter and a gap is present between the second blocker plate and the first blocker plate to permit flow of air around the second blocker plate. A third blocker plate is arranged downstream from the second blocker plate within the blocker cavity and includes a feed hole. Air within a region between the second blocker plate and the third blocker plate flows through the feed hole into the TOBI.

公开(公告)号：US12055067B2

公开(公告)日：2024-08-06

申请号：US18183079

申请日：2023-03-13

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Jon E. Sobanski

IPC: F01D5/14 ,  F01D5/08 ,  F01D5/18 ,  F01D5/28 ,  F01D9/04

CPC classification number: F01D5/187 ,  F01D5/081 ,  F01D5/14 ,  F01D5/147 ,  F01D5/18 ,  F01D5/282 ,  F01D9/041 ,  F05D2220/323 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2260/2214 ,  F05D2300/601 ,  F05D2300/603

Abstract: A method of fabricating a fiber-reinforced airfoil ring includes providing a mandrel that has a mandrel suction side and mandrel pressure side, and forming an endless braid around the mandrel. The endless braid conforms to the mandrel suction side and the mandrel pressure side. The endless braid is then consolidated with a matrix material. The mandrel is then removed, leaving the consolidated endless braid as a fiber-reinforced airfoil ring that has a suction side wall that extends between inner and outer platforms, a pressure side wall that extends between the inner and outer platforms, and suction and pressure side mate faces along, respectively, edges of the suction side wall and the pressure side wall, and at least one of the suction or pressure side mate faces includes protrusions along a trailing edge.

公开(公告)号：US20230313686A1

公开(公告)日：2023-10-05

申请号：US17973746

申请日：2022-10-26

Applicant: BEIHANG UNIVERSITY

Inventor： Xiang LUO ,  Zhe ZHANG ,  Dongdong LIU ,  Zeyu WU

IPC: F01D5/08 ,  H02J50/10

CPC classification number: F01D5/081 ,  H02J50/10

Abstract: Disclosed is an aero-engine turbine assembly, including a turbine assembly body and a cooling component. The turbine assembly body is provided with an internal flow passage, and the turbine assembly body includes a turbine rotor disk, a blade end wall and a turbine rotor blade, which are successively fixedly connected with each other. The internal flow passage passes through the turbine rotor disk, the blade end wall and the turbine motor blade, and the internal flow passage is provided with an inlet and an outlet. The cooling component is fixed on the turbine rotor disk, and the cooling component includes an electromagnetic pump system, an expansion joint and a radiator, which are successively communicated with each other. The electromagnetic pump system is communicated with the inlet, to inject liquid metal to into the internal flow passage.

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：US10082031B2

公开(公告)日：2018-09-25

申请号：US15059520

申请日：2016-03-03

Applicant: Rolls-Royce Deutschland Ltd & Co KG

Inventor： Markus Weinert ,  Tobias Leymann

IPC: F01D5/22 ,  F01D5/08 ,  F01D11/00 ,  F01D5/10

CPC classification number: F01D5/081 ,  F01D5/10 ,  F01D5/22 ,  F01D5/225 ,  F01D11/006 ,  F05D2240/55 ,  F05D2240/81 ,  F05D2260/201 ,  Y02T50/673 ,  Y02T50/676

Abstract: A rotor of a turbine of a gas turbine, having a rotor hub and a plurality of blade platforms, each carrying at least one turbine blade, and having one each cooling air chamber for passing cooling air formed by adjacent blade platforms. At least one damping element and/or sealing element is arranged radially beneath a platform intermediate gap provided between adjacent blade platforms. The cooling air chamber and/or the platform intermediate gap are designed such that starting from a side of the blade platform facing the adjacent blade platform, at least one outflow pocket open to the platform upper side and connected to the cooling air chamber is formed, and at least one cooling air pocket opened radially inwards to the cooling air chamber is provided in the wall of the cooling air chamber and opens towards the damping element and/or the sealing element or the platform intermediate gap.

公开(公告)号：US10072576B2

公开(公告)日：2018-09-11

申请号：US14546138

申请日：2014-11-18

Applicant: Mitsubishi Hitachi Power Systems, Ltd.

Inventor： Tomoyuki Matsui ,  Hayato Maekawa ,  Ryo Kawai

IPC: F02C7/18 ,  F01D5/08 ,  F01D5/18

CPC classification number: F02C7/18 ,  F01D5/081 ,  F01D5/187 ,  F05D2220/3212 ,  F05D2260/201 ,  Y02T50/676

Abstract: A gas turbine cooling system efficiently cools a first-stage turbine wheel and attachment portions of first-stage turbine blades. The gas turbine cooling system includes a group of impingement cooling holes provided in a partition wall as a stationary component that separates an exit space of a compressor and a wheel space located upstream of a turbine wheel for ejecting compressed air in the exit space toward the turbine wheel and attachment portions of the turbine blades.

公开(公告)号：US10060262B2

公开(公告)日：2018-08-28

申请号：US14895139

申请日：2014-05-28

Applicant: United Technologies Corporation

Inventor： Robert Knowlton ,  Max Asterlin ,  Brandon M. Rapp ,  Parth Jariwala

IPC: F01D5/10 ,  F01D11/00 ,  F01D5/18 ,  F01D5/26 ,  F01D5/08

CPC classification number: F01D5/10 ,  F01D5/081 ,  F01D5/18 ,  F01D5/26 ,  F01D11/006 ,  F05D2240/57 ,  F05D2260/96 ,  Y02T50/676

Abstract: A turbine blade vibration damper is described. The damper has an axially-extending main body defining an inner surface and opposed damping surface. The main body also has an edge spanning from the inner surface to the damping surface and slotted apertures extending through the main body. The slotted apertures extend between the inner surface and damping surface. Adjacent pairs of slotted apertures have elongated shapes defining longitudinal axes that intersect at a point off the surface of the damper.

公开(公告)号：US10005111B2

公开(公告)日：2018-06-26

申请号：US15005096

申请日：2016-01-25

Applicant: General Electric Company

Inventor： Michael Edward Eriksen ,  Matthew Bos ,  Nicole Jessica Tibbetts ,  Michael Scheper ,  Eric Zeltwanger

IPC: B08B9/00 ,  F01D5/08 ,  F01D5/18 ,  F01D25/00 ,  B08B7/02 ,  B24C3/32

CPC classification number: B08B9/00 ,  B08B7/02 ,  B24C3/327 ,  F01D5/081 ,  F01D5/186 ,  F01D25/002 ,  F05D2220/32 ,  F05D2230/72 ,  F05D2270/11 ,  Y02T50/672 ,  Y02T50/676

Abstract: A system and method of cleaning a turbine engine are provided. The method may include inserting, directing and evacuating a cleaning agent. Inserting may include inserting the cleaning agent through a predefined access port into a cooling cavity defined by an internal wall of an assembled turbine component, while directing may include directing the cleaning agent against the internal wall to remove a foreign material therefrom. Evacuating may include evacuating the cleaning agent from the cooling cavity.

公开(公告)号：US09995314B2

公开(公告)日：2018-06-12

申请号：US14803862

申请日：2015-07-20

Applicant: General Electric Company

Inventor： Brandon Wayne Miller ,  Jeffrey Anthony Hamel

IPC: F02C7/14 ,  F04D29/58 ,  F02C7/141 ,  F02C7/16 ,  F01D5/08 ,  F04D19/02 ,  F04D29/32 ,  F04D29/54

CPC classification number: F04D29/5846 ,  F01D5/081 ,  F02C7/14 ,  F02C7/141 ,  F02C7/16 ,  F04D19/02 ,  F04D29/324 ,  F04D29/541 ,  F05D2220/32 ,  F05D2260/212 ,  Y02T50/676

Abstract: A gas turbine engine including a compressor section and a turbine section, coupled by one or more shafts, is provided. The compressor section progressively compresses air and includes an aft-stage of rotor blades rotatable about an axial direction of the gas turbine engine. A cooling system is included with the gas turbine engine for cooling compressed air in or from the compressor section. The cooling system includes a fluid tank for storing a volume of cooling fluid and one or more fluid lines in fluid communication with the fluid tank. The one or more fluid lines include an outlet positioned adjacent to the aft-stage of rotor blades for injecting cooling fluid into the compressed air proximate the aft-stage of rotor blades.

公开(公告)号：US09995171B2

公开(公告)日：2018-06-12

申请号：US14598452

申请日：2015-01-16

Applicant: United Technologies Corporation

Inventor： Andrew D. Burdick ,  Anthony P. Cherolis ,  Christopher Treat ,  Jonathan Lemoine ,  Robert Russell Mayer ,  Jorge I. Farah ,  John H. Mosley

IPC: F01D25/12 ,  F01D5/02 ,  F01D25/26 ,  F01D5/08 ,  F01D9/06 ,  F02C7/12 ,  F01D25/16

CPC classification number: F01D25/12 ,  F01D5/02 ,  F01D5/081 ,  F01D9/065 ,  F01D25/125 ,  F01D25/162 ,  F01D25/26 ,  F02C7/12 ,  F05D2220/32 ,  F05D2260/2212 ,  Y02T50/673 ,  Y02T50/676

Abstract: A mid-turbine frame for a gas turbine engine includes an outer frame case and an inner frame case. At least one spoke connects the outer frame case to the inner frame case. The spoke includes an inlet passage with at least one branch that extends in an axial direction.