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公开(公告)号：US20180355760A1
公开(公告)日：2018-12-13
申请号：US15620134
申请日：2017-06-12
Applicant: General Electric Company
Inventor： Daniel Patrick Kerns , Mark Eugene Noe , Dennis Paul Dry , Brandon ALlanson Reynolds
CPC classification number: F01D25/246 , F05D2240/35 , F05D2300/177 , F05D2300/50212 , F05D2300/6033 , F23R3/002 , F23R3/50 , F23R3/60 , F23R2900/00018
Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.
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公开(公告)号：US11015613B2
公开(公告)日：2021-05-25
申请号：US15404608
申请日：2017-01-12
Applicant: General Electric Company
Inventor： Daniel Patrick Kerns , Dennis Paul Dry , Megan Elizabeth Scheitlin , Alexander Martin Sener , Jason David Shapiro
Abstract: A shroud assembly includes a shroud segment and a hanger. In one exemplary aspect, the shroud segment has a shroud body extending substantially along a circumferential direction between a first end and a second end. The shroud body defines a radial centerline along the circumferential direction. A flange is attached to or integral with the shroud body. The flange is pivotally coupled with the hanger at a location spaced from the radial centerline of the shroud body.
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公开(公告)号：US20220333491A1
公开(公告)日：2022-10-20
申请号：US17232721
申请日：2021-04-16
Applicant: General Electric Company
Inventor： Matthew Mark Weaver , Dennis Paul Dry , Todd William Bachmann
Abstract: An airfoil assembly for a turbine engine defines an axial direction, a radial direction, and a circumferential direction, and includes a first airfoil defining a first end along the radial direction, a first hub disposed on the first end of the first airfoil and having a first extension member extending at least partially in the radial direction, and a second airfoil adjacent to the first airfoil, the second airfoil defining a first end along the radial direction, a second hub disposed on the first end of the second airfoil and comprising a second extension member extending at least partially in the radial direction, and a circumferential bias assembly operable with the first extension member, the second extension member, or both for exerting a circumferential force on the first extension member, the second extension member, or both.
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公开(公告)号：US20190338676A1
公开(公告)日：2019-11-07
申请号：US16454975
申请日：2019-06-27
Applicant: General Electric Company
Inventor： Daniel Patrick Kerns , Mark Eugene Noe , Dennis Paul Dry , Brandon ALlanson Reynolds
Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.
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公开(公告)号：US20160290157A1
公开(公告)日：2016-10-06
申请号：US14674186
申请日：2015-03-31
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Wei Ning , Dennis Paul Dry , Mullahalli Venkataramaniah Srinivas
CPC classification number: F01D25/12 , F01D5/187 , F01D9/041 , F01D9/065 , F01D11/08 , F01D11/24 , F05D2220/30 , F05D2220/32 , F05D2240/11 , F05D2240/12 , F05D2240/30 , F05D2260/201 , F05D2260/202 , F05D2260/205 , Y02T50/672 , Y02T50/676
Abstract: In one aspect the present subject matter is directed to a system for cooling a turbine engine. The system includes a cooling medium source, a stator vane having an internal flow passage that is in fluid communication with the cooling medium source and a turbine shroud assembly having an internal flow passage that is in fluid communication with the internal flow passage of the stator vane. The system allows for reduced peak thermal gradients between a cooling medium provided by the cooling medium source and various turbine hardware components such as the turbine shroud assembly.
Abstract translation: 在一个方面，本主题涉及一种用于冷却涡轮发动机的系统。 该系统包括冷却介质源，具有与冷却介质源流体连通的内部流动通道的定子叶片和具有与定子叶片的内部流动通道流体连通的内部流动通道的涡轮机罩组件 。 该系统允许在由冷却介质源提供的冷却介质和各种涡轮机硬件部件（例如涡轮机罩组件）之间降低峰值热梯度。
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Patent Agency Ranking
公开(公告)号：US20240117756A1
公开(公告)日：2024-04-11
申请号：US18363797
申请日：2023-08-02
Applicant: General Electric Company
Inventor： Daniel Patrick Kerns , Mark Eugene Noe , Dennis Paul Dry , Brandon ALlanson Reynolds
CPC classification number: F01D25/246 , F01D25/28 , F23R3/002 , F23R3/50 , F23R3/60 , F05D2220/32 , F05D2240/35 , F05D2300/177 , F05D2300/50212 , F05D2300/6033 , F23R2900/00018
Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.
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公开(公告)号：US10385731B2
公开(公告)日：2019-08-20
申请号：US15620134
申请日：2017-06-12
Applicant: General Electric Company
Inventor： Daniel Patrick Kerns , Mark Eugene Noe , Dennis Paul Dry , Brandon ALlanson Reynolds
Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.
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8.发明申请公开(公告)号：US20190063250A1
公开(公告)日：2019-02-28
申请号：US15690307
申请日：2017-08-30
Applicant: General Electric Company
Inventor： Jinjie Shi , Dennis Paul Dry , Christopher Edward Wolfe , Andres Jose Garcia-Crespo , Yun Zhu
Abstract: Coating systems for a cooled turbine blade tip, such as a metal turbine blade tip, are provided. The coating system includes an abrasive layer overlying the surface of the turbine blade tip. One or more buffer layers may additionally be disposed between an outer surface of the blade tip and the abrasive layer. The coated blade tip can be used with a ceramic matrix composite (CMC) shroud coated with an environmental barrier coating (EBC) to provide improved cooling to the tip so as to lengthen oxidation time of the abrasive layer and reduce blade tip wear. Methods are also provided for forming the cooled blade tip and applying the coating system onto the cooled turbine blade tip.
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公开(公告)号：US20180195403A1
公开(公告)日：2018-07-12
申请号：US15404608
申请日：2017-01-12
Applicant: General Electric Company
Inventor： Daniel Patrick Kerns , Dennis Paul Dry , Megan Elizabeth Scheitlin , Alexander Martin Sener , Jason David Shapiro
CPC classification number: F04D29/526 , F01D11/08 , F01D25/246 , F04D29/083 , F05D2240/11 , F05D2250/411 , F05D2250/71 , F05D2250/75 , F05D2260/36 , F05D2300/6033 , Y02T50/672
Abstract: A shroud assembly includes a shroud segment and a hanger. In one exemplary aspect, the shroud segment has a shroud body extending substantially along a circumferential direction between a first end and a second end. The shroud body defines a radial centerline along the circumferential direction. A flange is attached to or integral with the shroud body. The flange is pivotally coupled with the hanger at a location spaced from the radial centerline of the shroud body.
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公开(公告)号：US11739663B2
公开(公告)日：2023-08-29
申请号：US16454975
申请日：2019-06-27
Applicant: General Electric Company
Inventor： Daniel Patrick Kerns , Mark Eugene Noe , Dennis Paul Dry , Brandon ALlanson Reynolds
CPC classification number: F01D25/246 , F01D25/28 , F23R3/002 , F23R3/50 , F23R3/60 , F05D2220/32 , F05D2240/35 , F05D2300/177 , F05D2300/50212 , F05D2300/6033 , F23R2900/00018
Abstract: A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.
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