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公开(公告)号：US12070811B2
公开(公告)日：2024-08-27
申请号：US17200988
申请日：2021-03-15
发明人： Daniel Lecuyer , Robert Huszar
CPC分类号： B23H9/10 , B23P15/008 , B23P15/04 , F01D5/3007 , F01D11/006 , F05D2230/12 , F05D2240/55 , F05D2240/80 , F05D2260/30 , Y10T29/4932 , Y10T29/49336
摘要： A blade for mounting on a rotor disc of a gas turbine engine includes platform segments between a airfoil and blade root and extending laterally from the blade, the platform segment having a curved profile defining a platform recess on a root side of the platform segment, the recess configured to cooperate with recesses of adjacent blades to define a blade pocket. A recessed region is defined in a rear surface of the blade root, and is configured to receive a complementary projection of the rotor disc upon mounting the blade on the rotor disc. The recessed region has a surface configured to abut a corresponding surface on the projection of the rotor disc to form a face seal. Methods of manufacturing such a rotor disc and of sealing a circumferential joint between such blades and the rotor disc are also disclosed.
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公开(公告)号：US11788543B2
公开(公告)日：2023-10-17
申请号：US17287351
申请日：2019-11-14
申请人： Ebara Corporation
发明人： Miwa Hidekura , Ryoken Yomogida
摘要： The impeller (1) includes a main plate (3) formed from a metal plate; and vanes (5) each formed from a metal plate. Each of the vanes (5) has a three-dimensional portion (5A) having a surface inclined with respect to a rotation axis (CA) of the impeller (1) and a two-dimensional portion (5B) having a surface parallel to the rotation axis (CA) of the impeller (1), and the two-dimensional portion (5B) is fixed to the main plate (3) by a first weld (10) formed by projection welding.
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公开(公告)号：US11752580B2
公开(公告)日：2023-09-12
申请号：US17853216
申请日：2022-06-29
CPC分类号： B23P15/04 , F02C7/00 , F05D2220/32 , F05D2230/232 , F05D2240/12 , F05D2240/30
摘要： A system is for bonding a cover sheet to a core to form or repair a dual wall structure. The system includes a cover sheet probe and an inner pedestal probe. A three dimensional contoured tip of the cover sheet probe abuts against a three dimensional contoured outer surface of the cover sheet opposite a pedestal of the core. The pedestal abuts the inner surface of the cover sheet. The inner pedestal probe may be coupled to the core to create a conductive electrical path from the cover sheet probe through at least part of the structure. A flow of electric power is controlled and supplied to the cover sheet probe to heat a junction between the area of the cover sheet abutting the pedestal and the pedestal. A heated area is created in the junction and fixedly couples the coversheet and the pedestal.
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公开(公告)号：US11655717B2
公开(公告)日：2023-05-23
申请号：US16951947
申请日：2020-11-18
CPC分类号： F01D5/187 , B23K1/0018 , F01D11/122 , B23P15/04 , F05D2220/32 , F05D2230/10 , F05D2230/237 , F05D2260/20
摘要： A gas turbine engine component may include an airfoil extending radially from a base to a blade tip, the airfoil including a pressure sidewall and a suction sidewall each extending between a leading edge and a trailing edge opposite the leading edge, an internal cooling circuit extending from the base to the blade tip; and a squealer tip. The squealer tip may include a first and a second squealer tip rail adjacent to the first squealer tip rail, and a squealer tip cap extending between the first and second squealer tip rails. The blade tip, the first and second squealer tip rails, and the squealer tip cap may define an internal squealer tip cooling channel. The blade tip may define a supply aperture that fluidly connect the internal cooling circuit and the internal squealer tip cooling channel.
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公开(公告)号：US20190186274A1
公开(公告)日：2019-06-20
申请号：US16191663
申请日：2018-11-15
申请人： ROLLS-ROYCE plc
发明人： Adrian L. HARDING
CPC分类号： F01D5/187 , B23P15/04 , F01D5/147 , F05D2230/21 , F05D2230/211 , F05D2230/237 , F05D2240/301 , F05D2260/20 , F05D2260/204
摘要： Aerofoil including: a body comprising first body portion and second body portion bonded to first body portion, first and second body portions having outer faces forming an outer surface of the aerofoil, and inner faces opposing the outer faces; a channel formed within the aerofoil by the inner faces of the first body portion and the second body portion; and a dividing sheet provided within the channel, such that a cooling passage is formed between the dividing sheet and the inner face of at least one of the first body portion and second body portion, cooling passage arranged to conduct cooling fluid adjacent the body, for cooling the body; wherein the body has a rear face and an opposing front face; and the dividing sheet extends parallel to at least a portion of a rear face of the body, such that the cooling passage formed parallel to the rear face.
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6.发明申请公开(公告)号：US20180257185A1
公开(公告)日：2018-09-13
申请号：US15759169
申请日：2015-09-10
CPC分类号： B23P15/04 , B21D53/78 , B23H5/04 , B23K26/0093 , B23K2101/001 , F01D5/147 , F01D5/28 , F04D29/289 , F04D29/324 , F05D2220/32 , F05D2230/20 , F05D2240/303
摘要： The invention proposes a method for producing a protective reinforcement for the leading edge (BA) or trailing edge of a blade (P), the leading edge (BA) or trailing edge being curved, the method comprising steps of flattening (102) a hollow tube (1) so as to form at least one fold line (6) extending along the tube (1), opening (104) the flattened tube (1) by cutting the tube (1) along a cutting line (8) opposite the fold line (6) with respect to the tube (1), so as to form two flanks (16, 18) linked at the fold line (6) and intended to be mounted on the pressure side and the suction side of the blade (P), the method being characterised by a preliminary step (100) of bending the hollow tube (1) carried out before the flattening (102) and adapted such that the fold line (6) after flattening (102) is curved and substantially matches the curved leading edge (BA) of the blade (P).
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公开(公告)号：US10060266B2
公开(公告)日：2018-08-28
申请号：US14768512
申请日：2013-11-08
发明人： James Cosby , Michael A. Weisse , Kwan Hui
CPC分类号： F01D5/18 , B23P15/04 , F01D5/147 , F04D29/324 , F05D2220/32 , F05D2220/36 , F05D2230/23 , F05D2230/60 , Y02T50/671 , Y02T50/676
摘要： Hollow fan blades for gas turbine engines are disclosed. The hollow fan blades include a body having a convex side and a concave side wherein the convex side has a cavity formed therein. The cavity is covered by two covers including an inner cover that may be adhered to the body of the fan blade assembly and an outer cover that may be adhered to the inner cover and/or the body of the fan blade assembly. The covers may be made of titanium, more than two covers may be employed and more than one cavity may be employed.
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公开(公告)号：US10053987B2
公开(公告)日：2018-08-21
申请号：US14929273
申请日：2015-10-31
CPC分类号： F01D5/187 , B23P15/04 , B23P2700/13 , F01D5/182 , F01D5/186 , F01D5/225 , F01D5/288 , F01D9/041 , F01D25/12 , F01D25/28 , F01D25/30 , F05D2220/32 , F05D2230/90 , F05D2260/202 , F05D2260/203 , F05D2260/204 , F05D2300/611 , Y10T29/4932 , Y10T29/49341 , Y10T29/49982 , Y10T428/13 , Y10T428/24314 , Y10T428/24322 , Y10T428/24521 , Y10T428/24562 , Y10T428/24612 , Y10T428/24636
摘要： A manufacturing method includes forming one or more grooves in a component that comprises a substrate with an outer surface. The substrate has at least one interior space. Each groove extends at least partially along the substrate and has a base and a top. The manufacturing method further includes applying a structural coating on at least a portion of the substrate and processing at least a portion of the surface of the structural coating so as to plastically deform the structural coating at least in the vicinity of the top of a respective groove, such that a gap across the top of the groove is reduced. A component is also disclosed and includes a structural coating disposed on at least a portion of a substrate, where the surface of the structural coating is faceted in the vicinity of the respective groove.
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公开(公告)号：US20180216626A1
公开(公告)日：2018-08-02
申请号：US15928246
申请日：2018-03-22
发明人： Daniel A. Bales , Thomas J. Watson
CPC分类号： F04D29/18 , B23K1/0018 , B23P15/04 , F01D5/147 , F04D29/023 , F04D29/20 , F04D29/324 , F05D2220/36 , F05D2230/237 , F05D2300/133 , F05D2300/173 , F05D2300/174
摘要： A fan blade includes first and second titanium alloy portions that are secured to one another with an aluminum alloy braze that contains manganese. The first titanium alloy portion includes ribs, a root, and at least a portion of an exterior airfoil contour of the fan blade. The second titanium alloy portion includes another portion of the exterior airfoil contour. The ribs are secured to the second titanium alloy portion with the aluminum alloy braze. The first titanium alloy portion includes a tip, and leading and trailing edges. The second titanium alloy portion has a perimeter that is arranged inboard of the root, the tip and the leading and trailing edges.
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公开(公告)号：US20180209283A1
公开(公告)日：2018-07-26
申请号：US15412945
申请日：2017-01-23
发明人： Srikanth Chandrudu Kottilingam , David Edward Schick , Jon Conrad Schaeffer , Steven J. Barnell , Brian Lee Tollison , Yan Cui
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , B22F3/008 , B22F3/1055 , B22F3/24 , B22F5/009 , B22F2003/242 , B22F2003/247 , B22F2003/248 , B22F2207/20 , B22F2998/00 , B23P6/005 , B23P15/04 , B33Y10/00 , B33Y80/00 , B33Y99/00 , F01D5/005 , F01D9/042 , F05D2230/20 , F05D2230/21 , F05D2230/22 , F05D2230/23 , F05D2230/31 , F05D2230/51 , F05D2230/60 , F05D2230/64 , F05D2230/70 , F05D2230/80 , Y02P10/295 , Y02T50/672
摘要： A multi-piece part includes multiple pieces fabricated via different types of fabrication processes, wherein the multiple parts are configured to be coupled to one another to form the assembly. At least one of the multiple parts is fabricated via an additive manufacturing method. The multi-piece part also includes a holder assembly that couples and holds together the multiple pieces of the multi-piece part, wherein the holder assembly comprises a reversible, mechanical-type coupling.
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