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公开(公告)号：US10301964B2
公开(公告)日：2019-05-28
申请号：US14620727
申请日：2015-02-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Atul Kohli
Abstract: One exemplary embodiment of this disclosure relates to a component for a gas turbine engine. The component includes a baffle provided in an internal cavity of the component. The baffle includes a wall having an orifice therethrough, and the baffle further includes a lobe extending from the wall and at least partially covering the orifice.
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公开(公告)号：US10294799B2
公开(公告)日：2019-05-21
申请号：US14853182
申请日：2015-09-14
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
Abstract: A rotor blade of a turbine engine may have internal passages to permit the travel of cooling air through the blade. These passages may include a tip flag, a serpentine channel, and a trailing edge channel. The tip flag may extend radially outward along the leading edge of the rotor blade and may turn axially aftward along the tip of the rotor blade. The tip flag may terminate forward of a portion of the serpentine channel and the trailing edge channel. Thus the tip flag may be a “partial tip flag.” The internal passages may be arranged to ameliorate the effect of ambient pressure variations, such as between the leading edge and the trailing edge of the rotor blade, on the flow travel of cooling air through the rotor blade.
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公开(公告)号：US20190040753A1
公开(公告)日：2019-02-07
申请号：US15982396
申请日：2018-05-17
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Jose R. Paulino
Abstract: A component for a gas turbine engine includes at least one airfoil that has a radially inner end and a radially outer end. A platform includes a radially outer surface that is attached to the radially inner end of the airfoil. A radially inner side of the platform includes a forward surface and an aft surface. A pocket is recessed into at least one of the forward surface and the aft surface. A cover plate covers the pocket and a seal is attached to the cover plate.
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公开(公告)号：US10184341B2
公开(公告)日：2019-01-22
申请号：US14824307
申请日：2015-08-12
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
Abstract: An airfoil according to an exemplary aspect of the present disclosure includes, among other things, an airfoil body that has an internal passage for conveying a fluid flow. The internal passage includes first and second passage sections and a turn section that connects the first and second passage sections. A baffle is located in the second passage section and the turn section. The baffle includes a wedge region situated in at least the turn section and is oriented to either divide or join the fluid flow through the turn section.
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公开(公告)号：US10166599B2
公开(公告)日：2019-01-01
申请号：US15036216
申请日：2014-10-28
Applicant: United Technologies Corporation
Inventor： Lea K. Castle , Brandon W. Spangler
IPC: B22C9/10 , B22C3/00 , B22C7/02 , B22C9/24 , B22C9/12 , B22D25/02 , B22D29/00 , B22D29/04 , F01D5/28 , F01D9/02
Abstract: A casting core assembly (140) includes a metallic core (144, 146, 148), a ceramic core (142) having a compartment (186) in which the portion of the metallic core is received, and a ceramic coating (260) at least partially covering the metallic core and the ceramic core.
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Patent Agency Ranking
公开(公告)号：US20180320531A1
公开(公告)日：2018-11-08
申请号：US15584106
申请日：2017-05-02
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Dominic J. Mongillo
CPC classification number: F01D5/187 , F01D5/147 , F01D9/041 , F05D2210/40 , F05D2220/32 , F05D2230/211 , F05D2240/125 , F05D2240/305 , F05D2240/306 , F05D2250/185 , F05D2260/22141
Abstract: Turn caps for airfoils of gas turbine engines having a first pressure-side turn passage extending from a respective inlet to a respective outlet within the turn cap, a first suction-side turn passage extending from a respective inlet to a respective outlet within the turn cap, and a merging chamber fluidly connected to the outlets of the first pressure-side turn passage and the first suction-side turn passage, wherein each of the first suction-side turn passage and the first pressure-side turn passage turn a direction of fluid flow from a first direction to a second direction such that a fluid flow exiting the first suction-side turn passage and the first pressure-side turn passage are aligned when entering the merging chamber.
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17.发明申请公开(公告)号：US20180245479A1
公开(公告)日：2018-08-30
申请号：US15968987
申请日：2018-05-02
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
CPC classification number: F01D25/12 , F01D9/042 , F01D25/14 , F01D25/246 , F05D2260/22141
Abstract: A gas turbine engine is provided. The gas turbine engine includes an engine casing structure and a part retained relative to the engine casing structure by a channel-cooled hook. The channel-cooled hook includes at least a portion of a hook cooling channel. A vane assembly for the gas turbine engine is also provided.
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公开(公告)号：US10041374B2
公开(公告)日：2018-08-07
申请号：US14665182
申请日：2015-03-23
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brandon W. Spangler , Ky H. Vu , Gina Cavallo
Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a platform and a feed cavity that feeds a cooling fluid inside of the platform. The feed cavity includes a leg portion and a main body portion that extends from the leg portion inside of the platform. A cooling cavity is inside the platform and in fluid communication with the feed cavity.
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公开(公告)号：US10036259B2
公开(公告)日：2018-07-31
申请号：US14929692
申请日：2015-11-02
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Laurie L. Burstynski
CPC classification number: F01D5/186 , F02C3/04 , F02C7/18 , F05D2220/3212 , F05D2240/81 , F05D2250/74 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: A turbine blade includes a platform that has a platform leading edge and trailing edge joined by two platform circumferential sides. An airfoil extends radially outwardly from the platform to a free tip end. The airfoil includes an airfoil leading edge and trailing edge joined by opposed pressure and suction sides. A root extends radially inwardly from the platform. The platform and the airfoil include film cooling holes arranged in substantial conformance with the Cartesian coordinates set forth in Table 1 herein. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate, and the cooling holes have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.0 mm).
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公开(公告)号：US09988913B2
公开(公告)日：2018-06-05
申请号：US14738001
申请日：2015-06-12
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler
CPC classification number: F01D5/188 , B23P15/02 , F01D5/282 , F01D5/284 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2230/10 , F05D2230/232 , F05D2230/60 , F05D2240/11 , F05D2240/12 , F05D2240/30 , F05D2240/35 , F05D2260/201 , F05D2260/221 , F05D2260/2212 , F05D2300/131 , F05D2300/20 , F05D2300/6033 , Y02T50/672 , Y02T50/676
Abstract: A method for forming a gas turbine engine component comprises the steps of forming a block of a high temperature alloy material. An external surface of the block is machined to form an external surface of a gas turbine engine component. At least one cooling passage within the component that is open to at least one end of the component is machined. At least one insert with a heat transfer feature is formed. The insert is installed within the at least one cooling passage. A component for a gas turbine engine is also disclosed.
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