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公开(公告)号：US11073024B2
公开(公告)日：2021-07-27
申请号：US16220396
申请日：2018-12-14
Applicant: United Technologies Corporation
Inventor： Christopher Perron , Justin M. Aniello , Shawn M. McMahon , Mohamed Hassan , Ricardo Trindade , Steven Bruce Gautschi , David Barger , Brett Alan Bartling , Nicholas J. Madonna , Robin Prenter , Ryan Lundgreen , Christopher Cosher
Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooing airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.
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公开(公告)号：US20190078786A1
公开(公告)日：2019-03-14
申请号：US15699163
申请日：2017-09-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tracy A. Propheter-Hinckley , Atul Kohli , Brandon W. Spangler , David J. Hyland , Dustin W. Davis , Ricardo Trindade , Stephen K. Kramer , Steven Bruce Gautschi
Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.
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公开(公告)号：US20190078785A1
公开(公告)日：2019-03-14
申请号：US15698967
申请日：2017-09-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tracy A. Propheter-Hinckley , Atul Kohli , Benjamin D. Bellows , Brandon W. Spangler , David J. Hyland , Dennis M. Moura , Dustin W. Davis , Mark F. Zelesky , Ricardo Trindade , Stephen K. Kramer , Steven Bruce Gautschi , Trevor Rudy
CPC classification number: F23R3/60 , F23R3/002 , F23R3/06 , F23R3/54 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
Abstract: A combustor panel may include an attachment feature. Because conventional attachment features of conventional combustor panels may be insufficiently cooled, the present disclosure provides various combustor configurations for reducing hotspots in the vicinity of attachment features and/or for providing cooling airflow to and in the vicinity of attachment features.
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公开(公告)号：US10954815B2
公开(公告)日：2021-03-23
申请号：US16589290
申请日：2019-10-01
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, Jr. , Ricardo Trindade , Nicholas M. LoRicco
Abstract: Divided baffles for a gas turbine engines are provided. The divided baffles include a baffle body having a first end and a second end, at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities, at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities, and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.
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公开(公告)号：US20200149415A1
公开(公告)日：2020-05-14
申请号：US16532603
申请日：2019-08-06
Applicant: United Technologies Corporation
Inventor： Allan N. Arisi , Ricardo Trindade , Dominic J. Mongillo , Tracy A. Propheter-Hinckley
IPC: F01D5/18
Abstract: An airfoil includes an airfoil section that has an airfoil wall that defines a leading end, an arced trailing end, and first and second sides that join the leading end and the arced trailing end. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity that includes an exit region that spans between the first and second ends and that opens through the arced trailing end. The exit region includes pedestals arranged in a plurality of longitudinal pedestal rows. At least one of the longitudinal pedestal rows is straight and at least one of the longitudinal pedestal rows is arced.
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Patent Agency Ranking
公开(公告)号：US10480347B2
公开(公告)日：2019-11-19
申请号：US15874070
申请日：2018-01-18
Applicant: United Technologies Corporation
Inventor： Dominic J. Mongillo, Jr. , Ricardo Trindade , Nicholas M. LoRicco
Abstract: Divided baffles for a gas turbine engines are provided. The divided baffles include a baffle body having a first end and a second end, at least one divider located within the baffle body and extending from the first end to the second end arranged to divide an interior of the baffle body into two or more feed cavities, at least one cap arranged at the first end to bound a first feed cavity of the two or more feed cavities, and at least one cap arranged at the second end to bound a second feed cavity of the two or more feed cavities.
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公开(公告)号：US20160131037A1
公开(公告)日：2016-05-12
申请号：US14900730
申请日：2014-07-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Ricardo Trindade
CPC classification number: F02C7/18 , F01D5/081 , F01D5/082 , F01D5/084 , F01D5/085 , F01D5/088 , F01D9/06 , F01D9/065 , F01D25/08 , F01D25/12 , F01D25/14 , F02C3/04 , F02C6/08 , F05D2220/32 , F05D2260/205 , F05D2260/232 , F05D2270/3062 , Y02T50/676
Abstract: In a featured embodiment, a gas turbine engine has a compressor section having a downstream rotor and a diffuser downstream of the compressor section. A combustor receives air downstream of the diffuser. A turbine section has at least one component to be cooled. A conduit is spaced from the diffuser and defines a cooling airflow path. The cooling airflow path is separate from an airflow downstream the diffuser, and passing to the combustor. The conduit passes cooling air to the component to be cooled.
Abstract translation: 在特征实施例中，燃气涡轮发动机具有压缩机部分，该压缩机部分具有在压缩机部分下游的下游转子和扩散器。 燃烧器在扩散器的下游接收空气。 涡轮部分具有至少一个待冷却的部件。 导管与扩散器间隔开并限定冷却气流路径。 冷却气流路径与扩散器下游的气流分离，并且通过燃烧器。 导管将冷却空气传递到要冷却的部件。
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公开(公告)号：US11078796B2
公开(公告)日：2021-08-03
申请号：US16220400
申请日：2018-12-14
Applicant: United Technologies Corporation
Inventor： Christopher Perron , Justin M. Aniello , Shawn M. McMahon , Ricardo Trindade , Steven Bruce Gautschi , David Barger , Brett Alan Bartling , Nicholas J. Madonna , Robin Prenter , Ryan Lundgreen , Christopher Cosher , Mohamed Hassan
Abstract: A vane ring for a gas turbine engine includes a multiple of vanes that extend between the inner vane platform and the outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a respective one of a multiple of feed passages; a multiple of metering passages in the outer vane platform, each of the multiple of metering passages in communication with the respective one of the multiple of feed passages; and a multiple of secondary passages in the outer vane platform, each of the multiple of secondary passages in communication with the respective one of the multiple of metering passages.
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公开(公告)号：US11008872B2
公开(公告)日：2021-05-18
申请号：US16220398
申请日：2018-12-14
Applicant: United Technologies Corporation
Inventor： Christopher Perron , Justin M. Aniello , Shawn M. McMahon , Ricardo Trindade , Steven Bruce Gautschi , David Barger , Brett Alan Bartling , Nicholas J. Madonna , Robin Prenter , Ryan Lundgreen , Christopher Cosher , Mohamed Hassan
Abstract: A vane ring for a gas turbine engine component includes a multiple of vanes that extend between an inner vane platform and an outer vane platform, each of the multiple of vanes contains an airfoil cooling circuit that receives cooling airflow through a feed passage located in the outer vane platform and an extension from the outer vane platform, the extension comprises a metering passage in communication with the feed passage.
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公开(公告)号：US20210054753A1
公开(公告)日：2021-02-25
申请号：US16531430
申请日：2019-08-05
Applicant: United Technologies Corporation
Inventor： Robin Prenter , Ricardo Trindade , Ryan Lundgreen
Abstract: A diffuser case for a gas turbine engine including: a pre-diffuser; a diffuser case defining a dump region, an inner shroud, and an outer shroud, the pre-diffuser being fluidly connected to the inner shroud and the outer shroud through the dump region; a tangential onboard injector module fluidly connected to the inner shroud through inlet orifice located in the diffuser case proximate an aft end of the inner shroud; and an inlet extender initiating at the inlet orifice of the tangential onboard injector module, extends through the inner shroud, and terminates at a distal end proximate the pre-diffuser.
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