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公开(公告)号：US11346239B2
公开(公告)日：2022-05-31
申请号：US17024975
申请日：2020-09-18
Applicant: Raytheon Technologies Corporation
Inventor： Shayan Ahmadian , Charles W. Haldeman , Mark F. Zelesky , Christopher T. Bergman , Sebastian Martinez
Abstract: A method of measuring a gas turbine engine component of a gas turbine engine according to an example of the present disclosure includes, among other things, providing at least one gas turbine engine component including a coating on a substrate, detecting infrared radiation emitted from at least one localized region of the coating at a first wavelength in a first electromagnetic radiation frequency range, detecting infrared radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength in a second electromagnetic radiation frequency range that differs from the first electromagnetic radiation frequency range, and determining a heat flux relating to the at least one localized region based upon a comparison of the first wavelength and the second wavelength.
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公开(公告)号：US12044146B2
公开(公告)日：2024-07-23
申请号：US18123526
申请日：2023-03-20
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Richard Wesley Jackson , Adam P. Generale , Xuan Liu , Mark F. Zelesky
IPC: F01D5/28
CPC classification number: F01D5/288 , F01D5/284 , F05D2220/32 , F05D2240/305 , F05D2240/306 , F05D2300/15 , F05D2300/21 , F05D2300/222 , F05D2300/30 , F05D2300/6033 , F05D2300/611 , F05D2300/6111
Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and suction and pressure sides that join the leading end and the trailing end. The airfoil wall is formed of a silicon-containing ceramic. A first environmental barrier topcoat is disposed on the suction side of the airfoil wall, and a second, different environmental barrier topcoat is disposed on the pressure side of the airfoil wall. The first topcoat is vaporization-resistant and the second topcoat is resistant to calcium-magnesium-aluminosilicate.
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公开(公告)号：US11680531B2
公开(公告)日：2023-06-20
申请号：US17682313
申请日：2022-02-28
Applicant: Raytheon Technologies Corporation
Inventor： Christopher J. Hanlon , James F. Krenzer , Becky E. Rose , Mark F. Zelesky
CPC classification number: F02C9/18 , F02C6/08 , F02C7/052 , F02C7/057 , F02C9/44 , F02K3/075 , F04D27/0215 , F05D2260/606 , F05D2260/607
Abstract: An aspect includes a system for a gas turbine engine. The system includes one or more bleeds of the gas turbine engine and a control system configured to check one or more activation conditions of a dirt rejection mode in the gas turbine engine. A bleed control schedule of the gas turbine engine is adjusted to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions. One or more deactivation conditions of the dirt rejection mode in the gas turbine engine are checked. The dirt rejection mode is deactivated to fully close the one or more bleeds based on the one or more deactivation conditions.
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公开(公告)号：US12152505B2
公开(公告)日：2024-11-26
申请号：US17994490
申请日：2022-11-28
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace , Mark F. Zelesky
Abstract: Disclosed is a method of reducing play in a vane arc segment. The vane arc segment includes an airfoil piece that defines first and second platforms and a hollow airfoil section that has an internal cavity and that extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a radial flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the radial flange, and a thermal insulation element is located adjacent the radial flange. The method includes performing a light scan of the radial flange to produce a digital three-dimensional model of the radial flange, and then machining the thermal insulation element in accordance with the digital three-dimensional model to provide a low-tolerance fit between the radial flange and the thermal insulation element that limits play between the airfoil piece and the thermal insulation element.
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公开(公告)号：US11078793B2
公开(公告)日：2021-08-03
申请号：US16574359
申请日：2019-09-18
Applicant: Raytheon Technologies Corporation
Inventor： Wolfgang Balzer , Thomas J. Praisner , Atul Kohli , Mark F. Zelesky , Dominic J. Mongillo, Jr.
Abstract: An airfoil for a gas turbine engine includes an airfoil with pressure and suction sides that are joined at leading and trailing edges. The airfoil extends a span from a support to an end in a radial direction. 0% span and 100% span positions respectively correspond to the airfoil at the support and at the end. The leading and trailing edges are spaced apart from one another an axial chord in an axial direction. A cross-section of the airfoil at a span location has a diameter tangent to the pressure and suction sides. The diameter corresponds to the largest circle fitting within the cross-section. A ratio of the diameter to the axial chord is at least 0.4 between 50% and 95% span location.
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Patent Agency Ranking
公开(公告)号：US20230250727A1
公开(公告)日：2023-08-10
申请号：US18123526
申请日：2023-03-20
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Richard Wesley Jackson , Adam P. Generale , Xuan Liu , Mark F. Zelesky
IPC: F01D5/28
CPC classification number: F01D5/288 , F01D5/284 , F05D2300/6033 , F05D2300/611 , F05D2300/30 , F05D2300/6111 , F05D2300/21 , F05D2240/306 , F05D2240/305 , F05D2300/222 , F05D2300/15 , F05D2220/32
Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, and suction and pressure sides that join the leading end and the trailing end. The airfoil wall is formed of a silicon-containing ceramic. A first environmental barrier topcoat is disposed on the suction side of the airfoil wall, and a second, different environmental barrier topcoat is disposed on the pressure side of the airfoil wall. The first topcoat is vaporization-resistant and the second topcoat is resistant to calcium-magnesium-aluminosilicate.
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公开(公告)号：US11536148B2
公开(公告)日：2022-12-27
申请号：US17102575
申请日：2020-11-24
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace , Mark F. Zelesky
Abstract: A vane arc segment includes an airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a first platform radial flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the first platform radial flange. A thermal insulation element is situated adjacent the first platform radial flange. The support hardware supports the airfoil piece through the thermal insulation element.
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公开(公告)号：US20210301676A1
公开(公告)日：2021-09-30
申请号：US17024975
申请日：2020-09-18
Applicant: Raytheon Technologies Corporation
Inventor： Shayan Ahmadian , Charles W. Haldeman , Mark F. Zelesky , Christopher T. Bergman , Sebastian Martinez
Abstract: A method of measuring a gas turbine engine component of a gas turbine engine according to an example of the present disclosure includes, among other things, providing at least one gas turbine engine component including a coating on a substrate, detecting infrared radiation emitted from at least one localized region of the coating at a first wavelength in a first electromagnetic radiation frequency range, detecting infrared radiation emitted from the substrate corresponding to the at least one localized region at a second, different wavelength in a second electromagnetic radiation frequency range that differs from the first electromagnetic radiation frequency range, and determining a heat flux relating to the at least one localized region based upon a comparison of the first wavelength and the second wavelength.
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公开(公告)号：US20220307427A1
公开(公告)日：2022-09-29
申请号：US17682313
申请日：2022-02-28
Applicant: Raytheon Technologies Corporation
Inventor： Christopher J. Hanlon , James F. Krenzer , Becky E. Rose , Mark F. Zelesky
Abstract: An aspect includes a system for a gas turbine engine. The system includes one or more bleeds of the gas turbine engine and a control system configured to check one or more activation conditions of a dirt rejection mode in the gas turbine engine. A bleed control schedule of the gas turbine engine is adjusted to extend a time to hold the one or more bleeds of the gas turbine engine partially open at a power setting above a threshold based on the one or more activation conditions. One or more deactivation conditions of the dirt rejection mode in the gas turbine engine are checked. The dirt rejection mode is deactivated to fully close the one or more bleeds based on the one or more deactivation conditions.
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公开(公告)号：US20220162945A1
公开(公告)日：2022-05-26
申请号：US17102575
申请日：2020-11-24
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Raymond Surace , Mark F. Zelesky
Abstract: A vane arc segment includes an airfoil piece that defines first and second platforms and an airfoil section that extends between the first and second platforms. The first platform defines a gaspath side, a non-gaspath side, and a first platform radial flange that projects from the non-gaspath side. Support hardware supports the airfoil piece via the first platform radial flange. A thermal insulation element is situated adjacent the first platform radial flange. The support hardware supports the airfoil piece through the thermal insulation element.
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