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公开(公告)号：US20200248564A1
公开(公告)日：2020-08-06
申请号：US16265567
申请日：2019-02-01
Applicant: Rolls-Royce plc
Inventor： Michael J. Whittle , Steven Hillier
Abstract: A turbine section adapted for use in a gas turbine engine includes a turbine case, a turbine wheel, and a turbine vane assembly. The turbine case is made from metallic materials. The turbine wheel is housed in the case. The turbine vane assembly is fixed to the case and configured to smooth and redirect air moving along a primary gas path of the turbine section.
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公开(公告)号：US20190242268A1
公开(公告)日：2019-08-08
申请号：US16385725
申请日：2019-04-16
Applicant: Rolls-Royce North American Technologies, Inc. , Rolls-Royce Corporation , Rolls-Royce plc
Inventor： Daniel K. Vetters , Aaron D. Sippel , David J. Thomas , Andrew J. Eifert , Paul A. Davis , Simon L. Jones , Peter Broadhead , Bruce E. Varney , Jeffrey A. Walston , Steven Hillier
CPC classification number: F01D11/122 , C04B35/803 , C04B35/806 , C04B35/83 , C04B2235/5252 , C04B2235/94 , F01D11/12 , F01D25/005 , F01D25/12 , F04D29/164 , F04D29/526 , F05D2220/32 , F05D2230/60 , F05D2240/11 , F05D2240/55 , F05D2260/22141 , F05D2260/52 , F05D2300/6033 , Y02T50/672
Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.
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公开(公告)号：US09581038B2
公开(公告)日：2017-02-28
申请号：US13945377
申请日：2013-07-18
Applicant: ROLLS-ROYCE PLC
Inventor： Steven Hillier , Dennis Jong
CPC classification number: F01D11/006 , F01D5/284 , F01D11/001 , F01D11/122 , F01D25/005 , F01D25/24 , F01D25/243 , F01D25/246 , F05D2300/6033
Abstract: A seal segment is positioned, in use, radially adjacent the rotor. The seal segment has first and second circumferentially spaced passageways each of which extends in the fore and aft direction. In use, a first support bar is contained within the first passageway, and a second support bar is contained within the second passageway. The first and second support bars being mountable to complementary formations provided by the casing of the engine. The first passageway is configured such that the seal segment is fixed relative to the first support bar in the radial and circumferential directions. The second passageway is configured such that the seal segment is fixed relative to the second support bar in the radial direction but allows relative movement of the seal segment and the second support bar in the circumferential direction to accommodate differential thermal expansion of the seal segment and the casing.
Abstract translation: 密封段在使用中定位成径向地邻近转子。 密封段具有第一和第二周向间隔开的通道，每个通道在前后方向上延伸。 在使用中，第一支撑杆容纳在第一通道内，第二支撑杆容纳在第二通道内。 第一和第二支撑杆可安装到由发动机壳体提供的互补结构。 第一通道构造成使得密封段在径向和圆周方向上相对于第一支撑杆固定。 第二通道被构造成使得密封段相对于第二支撑杆沿径向方向固定，但是允许密封段和第二支撑杆在圆周方向上的相对运动，以适应密封段的不同热膨胀和 套管。
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公开(公告)号：US09546562B2
公开(公告)日：2017-01-17
申请号：US14224952
申请日：2014-03-25
Applicant: ROLLS-ROYCE PLC
Inventor： Steven Hillier
CPC classification number: F01D11/122 , F01D5/28 , F01D5/284 , F01D9/04 , F01D11/08 , F01D25/005
Abstract: A seal segment is provided for a shroud ring of a rotor of a gas turbine engine. The seal segment is positioned, in use, radially adjacent the rotor. The seal segment includes a body portion having front and rear sides which each contain a respective slot that extends in the circumferential direction so that a respective hook formation is insertable into each slot for attaching the seal segment to the engine casing. The body portion is formed from continuous fiber reinforced ceramic matrix composite, reinforcing fibers of the composite wrapping around each slot so that, at the base of the slot, the reinforcing fibers are parallel to the surface of the body portion.
Abstract translation: 为燃气轮机的转子的护罩环提供密封段。 密封段在使用中位于转子的径向附近。 密封段包括主体部分，其具有前侧和后侧，每个主体部分包含沿圆周方向延伸的相应狭槽，使得相应的钩形结构可插入每个狭槽中，以将密封段附接到发动机壳体。 主体部分由连续的纤维增强陶瓷基复合材料形成，复合材料的增强纤维缠绕在每个槽周围，使得在槽的基部处，增强纤维平行于主体部分的表面。
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公开(公告)号：US11773730B2
公开(公告)日：2023-10-03
申请号：US17508314
申请日：2021-10-22
Inventor： Michael J. Whittle , Steven Hillier , Stephen Harris , Sungbo Shim
CPC classification number: F01D5/187 , C04B35/80 , C04B41/457 , F01D5/147 , F01D5/282 , F01D5/284 , F01D9/041 , C04B2235/616 , F05D2230/10 , F05D2230/21 , F05D2240/123 , F05D2240/124 , F05D2260/2212 , F05D2260/232 , F05D2300/6033
Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support and a turbine vane arranged around the support. The support is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support.
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Patent Agency Ranking
公开(公告)号：US20230130393A1
公开(公告)日：2023-04-27
申请号：US17508314
申请日：2021-10-22
Inventor： Michael J. Whittle , Steven Hillier , Stephen Harris , Sungbo Shim
Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a support and a turbine vane arranged around the support. The support is made of metallic materials. The turbine vane is made of ceramic matrix composite materials to insulate the metallic materials of the support.
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公开(公告)号：US10883376B2
公开(公告)日：2021-01-05
申请号：US16265565
申请日：2019-02-01
Applicant: Rolls-Royce plc
Inventor： Michael J. Whittle , Steven Hillier
Abstract: A turbine section adapted for use in a gas turbine engine includes a turbine case, a turbine wheel, and a turbine vane assembly. The turbine case is made from metallic materials. The turbine wheel is housed in the case. The turbine vane assembly is fixed to the case and configured to smooth and redirect air moving along a primary gas path of the turbine section.
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公开(公告)号：US10767493B2
公开(公告)日：2020-09-08
申请号：US16265567
申请日：2019-02-01
Applicant: Rolls-Royce plc
Inventor： Michael J. Whittle , Steven Hillier
Abstract: A turbine section adapted for use in a gas turbine engine includes a turbine case, a turbine wheel, and a turbine vane assembly. The turbine case is made from metallic materials. The turbine wheel is housed in the case. The turbine vane assembly is fixed to the case and configured to smooth and redirect air moving along a primary gas path of the turbine section.
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公开(公告)号：US10584605B2
公开(公告)日：2020-03-10
申请号：US15672991
申请日：2017-08-09
Applicant: Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc. , Rolls-Royce High Temperature Composites Inc. , Rolls-Royce plc
Inventor： Aaron D. Sippel , Ted J. Freeman , David J. Thomas , Joseph P. Lamusga , Brian J. Shoemaker , Steven Hillier
Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.
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公开(公告)号：US20170370240A1
公开(公告)日：2017-12-28
申请号：US15672991
申请日：2017-08-09
Applicant: Rolls-Royce Corporation , Rolls-Royce North American Technologies Inc. , Rolls-Royce High Temperature Composites Inc. , Rolls-Royce plc
Inventor： Aaron D. Sippel , Ted J. Freeman , David J. Thomas , Joseph P. Lamusga , Brian J. Shoemaker , Steven Hillier
CPC classification number: F01D11/005 , F01D5/225 , F01D5/24 , F01D9/04 , F01D11/008 , F01D25/246 , F01D25/26 , F01D25/265 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F05D2300/6033 , Y02T50/672
Abstract: A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.
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