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21.发明申请公开(公告)号：US20210172859A1
公开(公告)日：2021-06-10
申请号：US16706211
申请日：2019-12-06
Applicant: United Technologies Corporation
Inventor： Xuan Liu , Zhong Ouyang , Andrew DeBiccari , Nicholas M. LoRicco , William J. Brindley , Kathryn Macauley , Christopher J. Bischof
Abstract: A method is provided that involves rotational equipment that includes a case and a first rotor blade within the case. During the method, a probe is arranged within the case adjacent the first rotor blade. A magnetic characteristic of the first rotor blade is measured using the probe. Presence of internal corrosion within the first rotor blade is determined based on the measured magnetic characteristic.
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公开(公告)号：US10724381B2
公开(公告)日：2020-07-28
申请号：US15912906
申请日：2018-03-06
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco
Abstract: A component for a gas turbine engine, includes a component outer surface exposed to flowpath gases of the gas turbine engine, a cooling channel located in the component, and at least one channel rib located in the cooling channel extending across the cooling channel from a channel inner surface to a channel outer surface. A cooling slot extends from the cooling channel to a slot outlet at the component outer surface. The slot outlet has a radial width greater than an axial length.
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公开(公告)号：US10557375B2
公开(公告)日：2020-02-11
申请号：US15863101
申请日：2018-01-05
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco
Abstract: An airfoil for a gas turbine engine includes a cavity including an internal surface of an outer wall. A baffle is disposed within the cavity and spaced apart from the internal surface. A partition is disposed between the baffle and the internal surface to divide a space between the baffle and the internal surface into at least a first passage and a second passage. A gas turbine engine is also disclosed.
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公开(公告)号：US10443401B2
公开(公告)日：2019-10-15
申请号：US15255187
申请日：2016-09-02
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Mark A. Boeke , Richard M. Salzillo, Jr. , Jeffrey J. DeGray
Abstract: A cooled component for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis of the gas turbine engine. The internal ribs are disposed within an internal cavity defining cooling air passages within the cooled component. A plurality of cooling holes are arranged in rows with axial orientations alternating between a radially outboard bias directing cooling air radially outward and a radially inboard bias directing cooling air radially inward. Each of the cooling holes includes an internal opening in communication with one of the cooling air passages and an external opening open to an outer surface of the cooled component. The external opening of each of the plurality of cooling holes is disposed on a side opposite the internal rib relative to a corresponding internal opening. A gas turbine engine and a method of fabricating a turbine airfoil are also disclosed.
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公开(公告)号：US20190226343A1
公开(公告)日：2019-07-25
申请号：US15876579
申请日：2018-01-22
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Ricardo Trindade , Dominic J. Mongillo, JR.
Abstract: Components for gas turbine engines are provided. The components include a hot external wall that is exposed to hot gaspath air when installed within a gas turbine engine, and an interior impingement wall, wherein the interior impingement wall defines a feed cavity and at least one impingement cavity is defined between the impingement wall and the external wall. The impingement wall includes a plurality of impingement holes that fluidly connect the feed cavity to the at least one impingement cavity, the external wall includes a plurality of film holes that fluidly connect the at least one impingement cavity to an exterior surface of the external wall, and wherein the only source of cooling air within the at least one impingement cavity is the feed cavity.
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Patent Agency Ranking
26.发明申请公开(公告)号：US20190211690A1
公开(公告)日：2019-07-11
申请号：US15886054
申请日：2018-02-01
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Dominic J. Mongillo, JR.
CPC classification number: F01D9/065 , F05D2240/81 , F05D2250/75 , F05D2260/202 , F05D2260/204 , F05D2260/22141
Abstract: An airfoil includes pressure and suction side walls that extend in a chord-wise direction between leading and trailing edges. The pressure and suction side walls extend in a radial direction to provide an exterior airfoil surface. A main-body core cooling passage is arranged between the pressure and suction walls in a thickness direction and extends radially toward a platform. An airfoil skin cooling passage is arranged in one of the pressure and suction side walls to form a hot side wall and a cold side wall. The hot side wall defines a portion of the exterior airfoil surface and the cold side wall defines a portion of the core passage. The airfoil skin cooling passage extends to a platform skin cooling passage arranged in the platform. A resupply hole fluidly connects the main-body core cooling passage and at least one of the airfoil skin cooling passage and the platform skin cooling passage.
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公开(公告)号：US20190203612A1
公开(公告)日：2019-07-04
申请号：US15856232
申请日：2017-12-28
Applicant: United Technologies Corporation
Inventor： Shawn M. McMahon , Christopher Whitfield , Nicholas M. LoRicco , Steven Bruce Gautschi , Vincent E. Simms , Justin M. Aniello , Thomas Allwood , Richard M. Salzillo , Jeffery Scott Hembree, SR.
CPC classification number: F01D25/12 , F01D9/02 , F05D2220/32 , F05D2250/74 , F05D2260/202
Abstract: A vane includes a pair of airfoils having a plurality of film cooling holes that extend through an exterior surface of the airfoils, the plurality of film cooling holes including at least a first subset of film cooling holes, wherein the first subset of film cooling holes break through the exterior surface at geometric coordinates set forth herein. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
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公开(公告)号：US20180106156A1
公开(公告)日：2018-04-19
申请号：US15295268
申请日：2016-10-17
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Mark A. Boeke , Jeffrey J. DeGray , Richard M. Salzillo , Dominic J. Mongillo
CPC classification number: F01D9/065 , F05D2240/81 , F05D2250/74 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A vane includes a pair of airfoils that have a plurality of film cooling holes that extend through an exterior surface of the airfoils. Each plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each geometric coordinates is measured from a reference point on a leading edge rail of a platform of the vane.
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公开(公告)号：US20180066524A1
公开(公告)日：2018-03-08
申请号：US15255187
申请日：2016-09-02
Applicant: United Technologies Corporation
Inventor： Nicholas M. LoRicco , Mark A. Boeke , Richard M. Salzillo, JR. , Jeffrey J. DeGray
CPC classification number: F01D5/187 , F01D5/186 , F01D25/12 , F05D2220/32 , F05D2230/10 , F05D2230/21 , F05D2260/202 , F05D2260/221 , Y02T50/676
Abstract: A cooled component for a gas turbine engine includes a plurality of internal ribs extending substantially parallel to a longitudinal axis of the gas turbine engine. The internal ribs are disposed within an internal cavity defining cooling air passages within the cooled component. A plurality of cooling holes are arranged in rows with axial orientations alternating between a radially outboard bias directing cooling air radially outward and a radially inboard bias directing cooling air radially inward. Each of the cooling holes includes an internal opening in communication with one of the cooling air passages and an external opening open to an outer surface of the cooled component. The external opening of each of the plurality of cooling holes is disposed on a side opposite the internal rib relative to a corresponding internal opening. A gas turbine engine and a method of fabricating a turbine airfoil are also disclosed.
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公开(公告)号：US20160177767A1
公开(公告)日：2016-06-23
申请号：US14907461
申请日：2014-07-24
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas N. Slavens , Sasha M. Moore , Nicholas M. LoRicco
CPC classification number: F01D11/008 , F01D11/006 , F04D29/083 , F04D29/542 , F05D2220/32 , F05D2240/55 , F05D2250/75 , F16J15/06 , F16J15/062 , F16J15/0887
Abstract: This disclosure relates to a gas turbine engine including a first engine component and a second engine component. The first engine component has a mate face adjacent a mate face of the second engine component. The engine further includes a seal provided between the mate face of the first engine component and the mate face of the second engine component. The seal includes least one trough.
Abstract translation: 本公开涉及一种包括第一发动机部件和第二发动机部件的燃气涡轮发动机。 第一发动机部件具有与第二发动机部件的配合面相邻的配合面。 发动机还包括设置在第一发动机部件的配合面与第二发动机部件的配合面之间的密封件。 密封件包括至少一个槽。
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