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公开(公告)号：US10041364B2
公开(公告)日：2018-08-07
申请号：US14930764
申请日：2015-11-03
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jonathan Jeffery Eastwood , Dave J. Hyland , Timothy Dale
IPC: F01D1/00 , F01D9/04 , F01D9/06 , F01D25/24 , F02C3/13 , F02C6/08 , F01D25/16 , F02C3/14 , F02C9/18
Abstract: An inner diffuser case for a gas turbine engine may include a pre-diffuser including a plurality of struts. At least one of the struts may include an aperture therethrough. A cone may have a downstream end coupled to the pre-diffuser downstream of, and proximate to, the aperture. A skirt may have a forward end coupled to the pre-diffuser downstream of, and proximate to, the aperture. The forward end of the skirt may be axially aligned with the downstream end of the cone.
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公开(公告)号：US20190219484A1
公开(公告)日：2019-07-18
申请号：US16264760
申请日：2019-02-01
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Marnie A. Rizo , David P. Houston , David M. Nissley , Paul J. Hiester , Timothy Dale , Timothy B. Winfield , Madeline Campbell , James R. Midgley
Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.
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公开(公告)号：US10100675B2
公开(公告)日：2018-10-16
申请号：US14958287
申请日：2015-12-03
Applicant: United Technologies Corporation
Inventor： Jonathan J. Eastwood , Dave J. Hyland , Timothy Dale
Abstract: An outer diffuser case of a diffuser case assembly for use in a gas turbine engine may have a housing orientated about an engine axis, a forward flange projecting radially outward from the housing, a mid-flange spaced axially aft of the forward flange and projecting radially inward from the housing, and an aft flange projecting radially outward from the housing. The mid flange is spaced axially between the forward and aft flanges and is configured to detachably engage an inner diffuser case of the case assembly. The forward flange is configured to detachably engage a high pressure compressor and the aft flange is configured to detachably engage a high pressure turbine of the engine.
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公开(公告)号：US20180223691A1
公开(公告)日：2018-08-09
申请号：US15423731
申请日：2017-02-03
Applicant: United Technologies Corporation
Inventor： Timothy Dale
CPC classification number: F01D25/243 , F01D9/02 , F02K3/06 , F05D2220/32 , F05D2240/14 , F05D2260/30 , F05D2260/31
Abstract: A gas turbine engine and a flange are disclosed. The gas turbine engine includes a case, and a flange coupled to the case, the flange including a flange body, a fastener hole formed through the flange body, the fastener hole configured to receive a fastener, a radial slot formed through the flange body, wherein the radial slot is adjacent to the fastener hole, the radial slot defines a first portion of the flange body and a second portion of the flange body, and the radial slot prevents transfer of a hoop stress between the first portion and the second portion.
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公开(公告)号：US20160201511A1
公开(公告)日：2016-07-14
申请号：US14913621
申请日：2014-09-12
Inventor： Hoyt Y. Chang, JR. , Yusuke Ichihashi , Yohei Fujimoto , Timothy Dale
IPC: F01D25/24
Abstract: A case is provided for a gas turbine engine. The case includes a wall defining a through-hole. The case also includes first and second pockets adjacent to, and on opposite sides, of the through hole. A method of reducing stress in a case of a gas turbine engine is also provided that includes reducing stress about a through-hole by providing a concavity on each side of the through-hole.
Abstract translation: 提供了一种用于燃气涡轮发动机的壳体。 壳体包括限定通孔的壁。 壳体还包括与通孔相邻并且在相对侧上的第一和第二凹部。 还提供了一种在燃气轮机的情况下减小应力的方法，其包括通过在通孔的每一侧上设置凹陷来减小通孔周围的应力。
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Patent Agency Ranking
公开(公告)号：US10690006B2
公开(公告)日：2020-06-23
申请号：US14913621
申请日：2014-09-12
Inventor： Hoyt Y. Chang, Jr. , Yusuke Ichihashi , Yohei Fujimoto , Timothy Dale
Abstract: A case is provided for a gas turbine engine. The case includes a wall defining a through-hole. The case also includes first and second pockets adjacent to, and on opposite sides, of the through hole. A method of reducing stress in a case of a gas turbine engine is also provided that includes reducing stress about a through-hole by providing a concavity on each side of the through-hole.
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公开(公告)号：US10550725B2
公开(公告)日：2020-02-04
申请号：US15297459
申请日：2016-10-19
Applicant: United Technologies Corporation
Inventor： Jonathan J. Eastwood , Timothy Dale
Abstract: Aspects of the disclosure are directed to a system for an engine having an axial centerline, comprising: a diffuser case, a turbine case, and a turbine vane support, where the diffuser case and the turbine case are coupled to one another via a substantially radially oriented flange, where the turbine vane support includes a heat shield for the flange, and where the turbine vane support includes a radially outward projecting tab that couples to the turbine case via a radial interference fit.
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公开(公告)号：US20160265371A1
公开(公告)日：2016-09-15
申请号：US15029474
申请日：2014-10-31
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Timothy Dale , Swati G. Bhanderi
Abstract: A combustor section of a gas turbine engine has a diffuser case with a structural cone having variable wall thicknesses strategically located for reducing localized stress in the cone.
Abstract translation: 燃气涡轮发动机的燃烧器部分具有扩散器壳体，其具有可变壁厚度的结构锥体，其具有可定位的位置，用于减小锥体中的局部应力。
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公开(公告)号：US10704989B2
公开(公告)日：2020-07-07
申请号：US16264760
申请日：2019-02-01
Applicant: United Technologies Corporation
Inventor： Frederick M. Schwarz , Marnie A. Rizo , David P. Houston , David M. Nissley , Paul J. Hiester , Timothy Dale , Timothy B. Winfield , Madeline Campbell , James R. Midgley
Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.
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公开(公告)号：US10344623B2
公开(公告)日：2019-07-09
申请号：US14934435
申请日：2015-11-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jonathan Jeffery Eastwood , Dave J. Hyland , Timothy Dale
Abstract: A pre-diffuser of an inner diffuser case of a gas turbine engine may comprise an annular outer wall and an annular inner wall radially inside of the annular outer wall to define a passage for primary airflow therebetween. The pre-diffuser may further comprise at least one strut extending radially between the annular inner wall and the annular outer wall and at least one aperture formed in the strut that extends radially through the strut, the annular inner wall, and the annular outer wall. The pre-diffuser may further comprise at least one hollow cavity formed in the strut, and the hollow cavity may be separate from the aperture.
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