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公开(公告)号：US11879358B2
公开(公告)日：2024-01-23
申请号：US17772176
申请日：2020-11-27
申请人： EXONETIK TURBO INC.
CPC分类号： F01D5/284 , C04B35/44 , C04B35/48 , F01D5/08 , F01D5/18 , F01D5/288 , F01D25/12 , C04B2235/3222 , C04B2235/3225 , C04B2235/3246 , C04B2235/9607 , C04B2237/121 , C10M2201/0613 , F05D2230/90
摘要： A rim-rotor assembly has an annular structure including a composite rim and a hub. Blades project from the hub, tips of the blades contacting the annular structure, the blades configured to be loaded in compression against the annular structure. A thermal barrier is in the annular structure, the thermal barrier defining at least part of a radially inward surface of the annular structure. The tips of the blades contact the thermal barrier, the thermal barrier being a thermal barrier coating.
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公开(公告)号：US11674395B2
公开(公告)日：2023-06-13
申请号：US17024212
申请日：2020-09-17
发明人： Nicholas Joseph Kray , Nitesh Jain
摘要： A rotor disk for a gas turbine engine includes a disk body having a central bore extending therethrough. The disk body includes a bore body that extends around the central bore, a web that extends radially outward from the bore body having decreased thickness relative to the bore body and a peripheral rim that is located at an outer end of the web. The peripheral rim includes blade mounting structures for engaging complementary mounting structures of rotor blades. The bore body has a bore cavity that extends continuously through the bore body and about an entire periphery of the central bore. The bore cavity has a central axis that forms a circle about the central bore.
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3.发明申请公开(公告)号：US20190186268A1
公开(公告)日：2019-06-20
申请号：US16322963
申请日：2017-07-14
CPC分类号： F01D5/08 , F01D5/081 , F02C7/18 , F05D2240/81 , F05D2260/201
摘要： A turbomachine arrangement having a platform cooling device for a blade positioned at a platform of the blade. The cooling device's peripheral edge is in contact with the platform; a first surface portion forms a first cavity between the cooling device and platform and has impingement holes to impinge onto the platform; a second surface portion forms a second cavity between the cooling device and platform; a barrier in contact with the platform forms a connection between two sections of the edge and fluidically separates the first and second cavity. The cooling device is connected at the edge to the blade so the first and second cavity are formed between the cooling device and blade. The blade has a supply passage, connecting a hollow core and the second cavity for supplying cooling fluid to the second cavity and the first cavity is supplied with cooling fluid via the impingement holes.
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公开(公告)号：US20180258862A1
公开(公告)日：2018-09-13
申请号：US15979906
申请日：2018-05-15
CPC分类号： F02C9/18 , F01D5/08 , F01D5/082 , F01D9/065 , F01D11/24 , F01D25/10 , F02C3/34 , F02C7/125 , F05D2260/20 , F05D2260/941 , Y02T50/676
摘要： A gas-circulation system for conditioning a disk of an aircraft may comprise a first takeoff port configured to extract a combusted gas and a second takeoff port configured to extract an uncombusted gas. A first valve may comprise an inlet in fluid communication with the first and second takeoff ports and an outlet of the first valve in fluid communication with the disk.
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公开(公告)号：US20170370232A1
公开(公告)日：2017-12-28
申请号：US15544112
申请日：2015-01-22
申请人： Siemens Energy, Inc.
发明人： Ching-Pang Lee
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/08 , F01D5/186 , F01D5/20 , F05D2220/32 , F05D2240/307 , F05D2260/202 , F05D2260/2212
摘要： An internal cooling system (10) for an airfoil (12) in a turbine engine (14) whereby the cooling system (10) includes a chordwise extending tip cooling channel (16) radially inward of a squealer tip (18) and formed at least in part by an inner wall (20) with a nonlinear outer surface (22) is disclosed. The nonlinear outer surface (22) of the inner wall (20) of the chordwise extending tip cooling channel (16) may be formed from pressure and suction side sections (24, 26) that intersect at a point (74) that is closer to the inner surface (30) of an outer wall (32) forming at least a portion of the squealer tip (18) than other aspects of the pressure side section (24) and the suction side section (26). The configurations of the pressure and suction side sections (24, 26) reduces the flow cross-sectional area, which accelerates the cooling fluid flow in a chordwise direction within the chordwise extending tip cooling channel (16) and directs cooling fluid toward the pressure and suction side outer walls (34, 36) for improved cooling efficiency.
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公开(公告)号：US20170342904A1
公开(公告)日：2017-11-30
申请号：US15134653
申请日：2016-04-21
申请人： One Financial Plaza
CPC分类号： F02C7/18 , F01D5/08 , F01D5/18 , F01D9/065 , F01D25/28 , F02C3/045 , F02C6/08 , F02C7/12 , F02C7/20 , F05D2250/18 , Y02T50/675
摘要： A gas turbine engine according to an example of the present disclosure includes a fan situated at an inlet of a bypass passage. The fan has a fan diameter, Dfan. A low pressure turbine section is configured to drive the fan and a first compressor section. The low pressure turbine section has a greater number of stages than the first compressor section. The low pressure turbine section has a maximum rotor diameter, Dturb. A ratio of the maximum rotor diameter Dturb divided by the fan diameter Dfan is less than 0.6.
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公开(公告)号：US20170292455A1
公开(公告)日：2017-10-12
申请号：US15092008
申请日：2016-04-06
CPC分类号： F02C9/18 , F01D5/08 , F01D5/187 , F01D9/065 , F01D25/24 , F01D25/246 , F02C3/04 , F02C6/08 , F02C7/18 , F02C9/16 , F02K3/02 , F05D2220/32 , F05D2250/71 , F05D2260/231 , F05D2260/606 , F05D2260/96 , Y02T50/676
摘要： An air bypass system for a gas turbine engine includes a nozzle for a gas turbine engine. The air bypass system includes the nozzle having an inner band, an outer band, and an airfoil extending between the inner band and the outer band. The airfoil defines an internal passage. A diaphragm includes an inner wall, a first rail, and a second rail, which collectively define a diaphragm cavity. The first rail defines a first rail aperture. A manifold is positioned in the diaphragm cavity. The manifold and the diaphragm collectively define a manifold chamber in fluid communication with the first rail aperture. A tube extends through the internal passage defined by the airfoil and into the diaphragm cavity. The tube is in fluid communication with the manifold chamber. Compressed air flows through the tube into the manifold chamber and exits the chamber through the first rail aperture.
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公开(公告)号：US20170175244A1
公开(公告)日：2017-06-22
申请号：US14974755
申请日：2015-12-18
发明人： Andrew Joseph Detor , Leonardo Ajdelsztajn , Thomas Michael Bigelow , Richard Didomizio , Andrew William Emge , James Anthony Ruud , Michael James Weimer
IPC分类号： C23C4/073 , B22F9/16 , C22F1/10 , C22C19/07 , F01D25/00 , C23C4/129 , C23C4/123 , C23C4/134 , F01D5/08 , B22F9/04 , C22C30/00
CPC分类号： C23C4/073 , B22F1/0085 , B22F3/115 , B22F5/009 , B22F7/08 , B22F9/04 , B22F9/16 , B22F2301/052 , B22F2301/15 , B22F2301/20 , B22F2301/45 , C22C1/0433 , C22C19/00 , C22C19/07 , C22C30/00 , C22F1/10 , C23C4/123 , C23C4/129 , C23C4/134 , C23C24/04 , F01D5/08 , F01D25/007 , F05D2230/90 , F05D2240/24 , F05D2300/175 , F05D2300/177 , F05D2300/611 , Y10T428/12931 , Y10T428/12944
摘要： An article includes a substrate comprising a precipitate-strengthened alloy and a coating disposed over the substrate. The alloy comprises a) a population of gamma-prime precipitates, the population having a multimodal size distribution with at least one mode corresponding to a size of less than about 100 nanometers; or b) a population of gamma-double-prime precipitates having a median size less than about 300 nanometers. The coating comprises at least two elements, and further comprises a plurality of prior particles. At least a portion of the coating is substantially free of rapid solidification artifacts. Methods for fabricating the article and for processing powder useful for fabricating the article are also provided.
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公开(公告)号：US20170167384A1
公开(公告)日：2017-06-15
申请号：US14967518
申请日：2015-12-14
发明人： Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler , William K. Ackermann , Matthew R. Feulner , Om P. Sharma
CPC分类号： F02C7/18 , F01D5/08 , F02C3/04 , F02C7/143 , F02C7/185 , F02C9/18 , F02K3/06 , F04D27/0215 , F04D29/582 , F05D2220/32 , F05D2220/3219 , F05D2240/24 , F05D2260/205 , F05D2260/211 , F05D2260/213 , Y02T50/676
摘要： A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.
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公开(公告)号：US20170138198A1
公开(公告)日：2017-05-18
申请号：US15349394
申请日：2016-11-11
IPC分类号： F01D5/08
CPC分类号： F01D5/08 , B22F3/15 , B22F7/08 , C04B35/5615 , C04B35/5618 , C04B35/6455 , C04B41/009 , C04B2235/77 , C04B2235/80 , C04B2235/96 , C04B2235/9607 , C22C29/005 , C22C29/06 , C22C29/067 , C22C29/16 , C23C4/02 , C23C4/08 , C23C4/18 , C23C24/04 , C23C24/085 , F01D5/147 , F01D5/284 , F01D25/005 , F05D2220/32 , F05D2230/42 , F05D2300/2261 , F05D2300/2262 , F05D2300/701
摘要： The present disclosure relates to building very large gas turbines without changing rotor materials. The gas turbine part can include a structure composed of a metal and a ternary ceramic called MAX phase, having a formula Mn+1AXn, where n=1, 2, or 3, M is an early transition metal such as Ti, V, Cr, Zr, Nb, Mo, Hf, Sc, Ta, and A is an A-group element such as Al, Si, P, S, Ga, Ge, As, Cd, In, Sn, Tl, Pb, and X is C and/or N.
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