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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
发明人： Raymond Surace , Eric A. Hudson
摘要： 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：US10662779B2
公开(公告)日：2020-05-26
申请号：US15353855
申请日：2016-11-17
摘要： A gas turbine engine component includes a passage and a wall adjacent the passage. The wall includes a first side bordering the passage and a second side opposite the first side. The second side includes an array of cells. The wall also includes an array of channels. Each of the channels is located proximate a corresponding one of the cells. A coating is disposed over the cells. When the coating degrades the channels open to permit impingement air flow through the channel onto sidewalls of the cells.
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公开(公告)号：US20200024970A1
公开(公告)日：2020-01-23
申请号：US16397180
申请日：2019-04-29
摘要： An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.
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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
发明人： Raymond Surace , Eric A. Hudson
CPC分类号： F01D17/162 , F01D9/065 , F01D11/24 , F01D17/16 , F02C7/12 , F05D2260/205
摘要： 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：US10094232B2
公开(公告)日：2018-10-09
申请号：US14825812
申请日：2015-08-13
摘要： Aspects of the disclosure are directed to a seal comprising: a shoe, and at least one beam coupled to the shoe, wherein the seal includes a single crystal material with a predetermined crystalline orientation. Aspects of the disclosure are directed to a method for designing a seal, comprising: obtaining a requirement associated with at least one of: a geometrical profile of the seal, a temperature range over which the seal is to operate, a natural frequency associated with the seal, or a range of deflection associated with the seal, selecting a crystalline orientation for a single crystal material of the seal based on the requirement, and fabricating the seal based on the selected crystalline orientation.
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公开(公告)号：US20180135458A1
公开(公告)日：2018-05-17
申请号：US15353855
申请日：2016-11-17
IPC分类号： F01D25/12 , F01D9/04 , F01D25/00 , F01D11/08 , F02C3/04 , F04D29/08 , F04D29/54 , F04D29/58 , F04D29/02
摘要： A gas turbine engine component includes a passage and a wall adjacent the passage. The wall includes a first side bordering the passage and a second side opposite the first side. The second side includes an array of cells. The wall also includes an array of channels. Each of the channels is located proximate a corresponding one of the cells. A coating is disposed over the cells. When the coating degrades the channels open to permit impingement air flow through the channel onto sidewalls of the cells.
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公开(公告)号：US20180128115A1
公开(公告)日：2018-05-10
申请号：US15866134
申请日：2018-01-09
CPC分类号： F01D5/187 , B22C9/10 , B22C9/108 , B22C9/24 , F01D5/186 , F05D2230/211 , F05D2260/204 , F05D2260/2212
摘要： An airfoil includes leading and trailing edges; first and second sides extending from the leading edge to the trailing edge, each side having an exterior surface; a core passage located between the first and second sides and the leading and trailing edges; and a wall structure located between the core passage and the exterior surface of the first side. The wall structure includes a plurality of cooling fluid inlets communicating with the core passage for receiving cooling fluid from the core passage, a plurality of cooling fluid outlets on the exterior surface of the first side for expelling cooling fluid and forming a cooling film along the exterior surface of the first side, and a plurality of cooling passages communicating with the plurality of cooling fluid inlets and the plurality of cooling fluid outlets. At least a portion of one cooling passage extends between adjacent cooling fluid outlets.
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8.发明申请公开(公告)号：US20150345383A1
公开(公告)日：2015-12-03
申请号：US14760810
申请日：2014-02-19
CPC分类号： F02C3/073 , F02C3/107 , F02C3/14 , F02C7/24 , F02K3/025 , F02K3/06 , F05D2220/32 , F05D2230/52 , F05D2230/60 , Y10T29/49236
摘要： A method of manufacturing a military engine includes the steps of designing a commercial engine core, including a combustor, a high pressure compressor driven by a high pressure turbine, and a low pressure turbine designed to drive a low pressure compressor, and a fan through a gear reduction. A high speed fan is attached to the low pressure turbine, such that the combustor, high pressure compressor, low and high pressure turbines from an engine designed for commercial purposes is utilized for military purposes. A gas turbine engine is also disclosed.
摘要翻译： 一种制造军用发动机的方法包括以下步骤：设计包括燃烧器，由高压汽轮机驱动的高压压缩机和设计成驱动低压压缩机的低压涡轮机的商业发动机芯，以及风扇通过 齿轮减速。 将高速风扇连接到低压涡轮机，使得用于商业目的的发动机的燃烧器，高压压缩机，低压和高压涡轮机用于军事目的。 还公开了一种燃气涡轮发动机。
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公开(公告)号：US10781716B2
公开(公告)日：2020-09-22
申请号：US16253038
申请日：2019-01-21
发明人： Susan M. Tholen , Dominic J. Mongillo , Paul M. Lutjen , James N. Knapp , Virginia L. Ross , Jonathan J. Earl , Eric A. Hudson
摘要： A cooling scheme for a blade outer air seal includes a perimeter cooling arrangement configured to convectively cool a perimeter of the blade outer air seal, and a core cooling arrangement configured to cool a central portion of the blade outer air seal through impingement cooling and to provide film cooling to an inner diameter face of the blade outer air seal.
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公开(公告)号：US10399189B2
公开(公告)日：2019-09-03
申请号：US15289801
申请日：2016-10-10
发明人： Eric A. Hudson , Alan C. Barron , Edwin Otero
摘要： A method of manufacturing an airfoil. The method includes fixing the airfoil in a workpiece space, detecting a position of the airfoil in the workpiece space using a force-sensing element, and removing material from the airfoil to reduce a dimension of the airfoil. In various embodiments, detecting the position of the airfoil includes moving the force-sensing element across a surface of the airfoil. For example, the surface of the airfoil may be a first surface, wherein removing material from the airfoil to reduce the dimension of the airfoil comprises removing material from a second surface of the airfoil opposite the first surface. Removing material from the second surface of the airfoil may be performed without moving the force-sensing element across the second surface of the airfoil.
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