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公开(公告)号：US11773742B2
公开(公告)日：2023-10-03
申请号：US16806168
申请日：2020-03-02
Applicant: United Technologies Corporation
Inventor： Jonathan Ortiz , Raymond Surace , Renee J. Jurek , Tracy A. Propheter-Hinckley
CPC classification number: F01D11/20 , F01D5/02 , F01D9/065 , F01D11/24 , F02C3/04 , F02C9/18 , F04D29/542 , F05D2220/32 , F05D2240/35 , F05D2260/213 , F05D2300/50212 , Y02T50/60
Abstract: A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.
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公开(公告)号：US11015457B2
公开(公告)日：2021-05-25
申请号：US16202483
申请日：2018-11-28
Applicant: United Technologies Corporation
Inventor： Christopher J. Peters , Emma J. Place , Jeffrey J. DeGray , Dominic J. Mongillo , Timothy J. Jennings , Raymond Surace , Jeremy B. Fredette
Abstract: A method of forming an airfoil, includes forming a hybrid skin core, a tip flag core, and a trailing edge core. The hybrid skin core, tip flag core, and trailing edge core are connected to form a first core portion. A leading edge core and a serpentine core are formed. The first core portion, the leading edge core, and the serpentine core are assembled together to form an airfoil core. An airfoil is formed around the airfoil core.
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公开(公告)号：US10815819B2
公开(公告)日：2020-10-27
申请号：US16161593
申请日：2018-10-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Raymond Surace , Eric A. Hudson
Abstract: A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a variable vane assembly and a secondary flow system associated with the variable vane assembly. Flow modulation of a cooling fluid through the secondary flow system is changed simultaneously with actuation of the variable vane assembly.
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公开(公告)号：US10563771B2
公开(公告)日：2020-02-18
申请号：US15092793
申请日：2016-04-07
Applicant: United Technologies Corporation
Inventor： Jeremy Drake , Raymond Surace
IPC: F16J15/3288 , F01D11/00 , F01D11/12 , F04D29/08
Abstract: Aspects of the disclosure are directed to a brush seal comprising: a first plate, a wire mesh adjacent the first plate, a bristle pack adjacent the wire mesh, and a second plate adjacent the bristle pack. Aspects of the disclosure are directed to a method comprising: positioning a wire mesh adjacent to a first plate, positioning a bristle pack adjacent to the wire mesh, positioning a second plate adjacent to the bristle pack, applying a toolset to hold the first plate, the wire mesh, the bristle pack, and the second plate in a stack-up, and performing an operation to form a brush seal from the stack-up of the first plate, the wire mesh, the bristle pack, and the second plate.
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公开(公告)号：US20200049256A1
公开(公告)日：2020-02-13
申请号：US16598168
申请日：2019-10-10
Applicant: United Technologies Corporation
Inventor： Jeremy Drake , Raymond Surace
IPC: F16J15/3288 , F04D29/08 , F01D11/12 , F01D11/00
Abstract: Aspects of the disclosure are directed to a brush seal comprising: a first plate, a wire mesh adjacent the first plate, a bristle pack adjacent the wire mesh, and a second plate adjacent the bristle pack. Aspects of the disclosure are directed to a method comprising: positioning a wire mesh adjacent to a first plate, positioning a bristle pack adjacent to the wire mesh, positioning a second plate adjacent to the bristle pack, applying a toolset to hold the first plate, the wire mesh, the bristle pack, and the second plate in a stack-up, and performing an operation to form a brush seal from the stack-up of the first plate, the wire mesh, the bristle pack, and the second plate.
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Patent Agency Ranking
公开(公告)号：US20190211695A1
公开(公告)日：2019-07-11
申请号：US15863158
申请日：2018-01-05
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Raymond Surace
CPC classification number: B28B7/342 , B28B7/16 , B28B7/18 , B32B18/00 , C04B2235/6028 , C04B2237/38 , C04B2237/62 , F01D5/18
Abstract: A method for forming a passage in a ceramic matrix composite component includes forming a core for a ceramic matrix composite component; embedding a hollow member into the core at a desired location for a passage in the ceramic matrix composite component; wrapping the core with a ceramic material; and inserting a rod through the hollow member and into the core.
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公开(公告)号：US20190048739A1
公开(公告)日：2019-02-14
申请号：US16161593
申请日：2018-10-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Raymond Surace , Eric A. Hudson
CPC classification number: F01D17/162 , F01D9/065 , F01D11/24 , F01D17/16 , F02C7/12 , F05D2260/205
Abstract: A variable area turbine arrangement according to an exemplary aspect of the present disclosure includes, among other things, a variable vane assembly and a secondary flow system associated with the variable vane assembly. Flow modulation of a cooling fluid through the secondary flow system is changed simultaneously with actuation of the variable vane assembly.
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公开(公告)号：US20160237845A1
公开(公告)日：2016-08-18
申请号：US15027526
申请日：2014-10-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： John D. Teixeira , Eric A. Grover , Raymond Surace
IPC: F01D17/16
CPC classification number: F01D17/162 , F01D5/143 , F05D2250/241 , F05D2250/711 , F05D2250/712 , Y02T50/673
Abstract: A gas turbine engine component includes an outer diameter endwall, an inner diameter endwall spaced radially inward of the outer diameter endwall, and at least one body supported between the outer and inner endwalls for rotation about an axis. The body includes an outer diameter surface spaced from the outer diameter endwall by a first gap and an inner diameter surface spaced from the inner diameter endwall by a second gap. The outer and inner diameter surfaces and the outer and inner diameter endwalls are configured such that the first and second gaps remain generally constant in size as the body rotates about the axis.
Abstract translation: 燃气涡轮发动机部件包括外径端壁，位于外径端壁的径向内侧的内径端壁，以及支撑在外端壁与内端壁之间的至少一个主体，用于绕轴线转动。 主体包括通过第一间隙与外径端壁隔开的外径表面，以及通过第二间隙与内径端壁隔开的内径表面。 外径和内径表面以及外径和内径端壁构造成使得当主体围绕轴线旋转时，第一和第二间隙的尺寸基本保持不变。
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公开(公告)号：US11591915B2
公开(公告)日：2023-02-28
申请号：US16587684
申请日：2019-09-30
Applicant: United Technologies Corporation
Inventor： Renee Behlman , Tracy Propheter-Hinckley , Raymond Surace , Matthew Devore
Abstract: A flowpath component for a gas turbine engine includes a body having a leading edge and a trailing edge. A first exterior wall connects the leading edge to the trailing edge and a second exterior wall connects the leading edge to the trailing edge. At least one first internal cooling passage has a first inlet at a first end of the body. At least one second internal cooling passage has a second inlet at a second end of the body. The at least one first internal cooling passage is isolated from the at least one second internal cooling passage.
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公开(公告)号：US20200347741A1
公开(公告)日：2020-11-05
申请号：US16806168
申请日：2020-03-02
Applicant: United Technologies Corporation
Inventor： Jonathan Ortiz , Raymond Surace , Renee J. Jurek , Tracy A. Propheter-Hinckley
Abstract: A gas turbine engine according to an example of the present disclosure include a compressor section, a combustor, and a turbine section. The combustor has a radially outer surface that defines a diffuser chamber radially outwardly of the combustor. The turbine section has a high pressure turbine first stage blade that has an outer tip, and a blade outer air seal positioned radially outwardly of the outer tip. A tap for tapping air has been compressed by the compressor and is passed through a heat exchanger. The air downstream of the heat exchanger passes through at least one pipe and into a manifold radially outward of the blade outer air seal, and then passes across the blade outer air seal to cool the blade outer air seal.
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