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公开(公告)号：US20240280054A1
公开(公告)日：2024-08-22
申请号：US18333597
申请日：2023-06-13
CPC分类号： F02C7/24 , B32B1/08 , B32B3/28 , B32B9/005 , B32B9/041 , B32B2250/04 , B32B2255/20 , B32B2307/304 , B32B2307/416 , B32B2307/418 , F05D2240/15 , F05D2260/231
摘要： A thermal insulation assembly for a duct through which high temperature fluid, greater than 500 Fahrenheit, passes. The thermal insulation assembly can experience pressures less than 80 kilopascals and can be included in a turbine engine. The thermal insulation assembly includes a first foil layer confronting the duct, a second foil layer spaced from the first foil layer, an insulation layer between the first foil layer and the second foil layer, an opacifier layer provided on the insulation layer, and a reflective layer applied to the opacifier layer.
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公开(公告)号：US20240208676A1
公开(公告)日：2024-06-27
申请号：US18554587
申请日：2022-04-13
CPC分类号： B64G1/58 , F02K9/88 , B64G1/006 , F05D2220/80 , F05D2240/15 , F05D2250/73
摘要： A heat shield for protecting a windward side of a vehicle from a high enthalpy flow is disclosed. The heat shield includes a centerbody sidewall and a centerbody base extending aft of the centerbody sidewall. The centerbody sidewall and the centerbody base define a heat shield outer surface that is non-axisym metric. Also disclosed is an aerospike nozzle defined at least partially by the heat shield, an engine including a high pressure chamber and the aerospike nozzle, and a vehicle including the engine.
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公开(公告)号：US11965427B1
公开(公告)日：2024-04-23
申请号：US17956881
申请日：2022-09-30
发明人： Thomas E. Clark , Marc J. Muldoon
CPC分类号： F01D25/145 , F01D11/005 , F05D2240/15 , F05D2260/231 , F05D2260/232 , F05D2260/30 , F05D2260/60 , F05D2300/175
摘要： A gas turbine engine includes a primary flow path fluidly connecting a compressor section, a combustor section and a turbine section. A cooling air flowpath is disposed radially outward of the primary flowpath. A first seal spans from an inner diameter of the cooling air flowpath to an outer diameter of the cooling air flowpath. The first seal includes at least one axial convolution and a plurality of pass through features defining a purge airflow. A heat shield is positioned immediately downstream of the first seal and is configured in relation to the first seal such that the purge airflow enters a mixing plenum defined between the heat shield and the first seal.
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公开(公告)号：US20240125250A1
公开(公告)日：2024-04-18
申请号：US18077492
申请日：2022-12-08
申请人： BorgWarner Inc.
发明人： Daniel Geisweid , Patrick Weber , Thomas Koerner
CPC分类号： F01D25/145 , F02B33/40 , F02B39/00 , F05D2230/60 , F05D2240/15 , F05D2250/231
摘要： The present invention relates to a heat shield (100) for a supercharging device (1), comprising a first ring portion (110), which is situated at the outside in a radial direction (24) and which is designed to bear the heat shield (100), and a second ring portion (120), which is situated at the inside in a radial direction (24) and which extends from the first ring portion (110). The second ring portion (120) has at least one structure-stiffening feature (200), the at least one structure-stiffening feature (200) being of bead-like form.
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公开(公告)号：US11873762B2
公开(公告)日：2024-01-16
申请号：US17317357
申请日：2021-05-11
CPC分类号： F02C7/24 , F01D25/145 , F05D2220/323 , F05D2240/15
摘要： A heat shield assembly adapted for use with gas turbine engines, airframes, and aircraft includes a carrier and a heat-shield tile. The carrier is adapted to couple to the gas turbine engine, airframe, or aircraft. The heat-shield tile includes material different than the carrier and is arranged to cover the carrier to protect the carrier from high-temperature gases surrounding the heat shield assembly.
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公开(公告)号：US20230399981A1
公开(公告)日：2023-12-14
申请号：US17806161
申请日：2022-06-09
发明人： Christopher GOVER
CPC分类号： F02C7/24 , B64D27/10 , F05D2220/323 , F05D2240/15 , F05D2300/121 , F05D2300/133 , F05D2300/603
摘要： A containment assembly is provided for an aircraft engine having a rotor with a set of blades. The containment assembly comprises a containment casing annularly surrounding the rotor radially outward of the set of blades. The containment casing is made of a material having a density less than that of steel. A layer of thermal insulation is disposed radially inward of the containment casing. The layer of thermal insulation is radially disposed between the containment casing and the set of blades.
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公开(公告)号：US20180258791A1
公开(公告)日：2018-09-13
申请号：US15455634
申请日：2017-03-10
发明人： Srikanth Chandrudu KOTTILINGAM , Brian Lee TOLLISON , David Edward SCHICK , Yan CUI , Surinder Singh PABLA , Jon Conrad SCHAEFFER
CPC分类号： F01D25/12 , C23C4/04 , C23C4/12 , F01D5/288 , F01D25/005 , F05D2220/32 , F05D2230/90 , F05D2240/15 , F05D2260/232 , F05D2260/36 , F05D2300/6033 , F05D2300/611 , F23M2900/05004 , F23R3/002 , F23R3/007 , F23R2900/00018
摘要： A component having a hybrid coating system is provided. The component includes a substrate having a surface and a hybrid coating system including a sheet disposed on the surface and a skin. The sheet includes a plurality of interlocking members. The skin includes a plurality of features corresponding to the interlocking members. The skin is engaged to the sheet in an interlocking manner via the interlocking members and the features. A method for forming a component with a hybrid coating system is also disclosed.
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公开(公告)号：US10036281B2
公开(公告)日：2018-07-31
申请号：US14847363
申请日：2015-09-08
发明人： Michael G. McCaffrey
CPC分类号： F01D25/246 , F01D9/041 , F01D25/162 , F05D2220/32 , F05D2240/15 , F05D2300/20 , F05D2300/6033 , Y10T29/49337
摘要： A mid-turbine frame for a gas turbine engine includes a CMC outer ring, a CMC inner ring, and a multiple of CMC airfoils between the CMC outer ring and the CMC inner ring. Each of the CMC airfoils includes at least one hollow tube and a shell of a multiple of CMC plies surrounding the hollow tube. The hollow tube reinforces the shell. A spring biased tie-rod assembly is mounted through at least one of the multiple of CMC airfoils.
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公开(公告)号：US09957820B2
公开(公告)日：2018-05-01
申请号：US14728723
申请日：2015-06-02
发明人： Benjamin F. Hagan , Ryan Alan Waite
CPC分类号： F01D9/02 , F01D5/188 , F01D5/189 , F01D9/023 , F05D2220/32 , F05D2240/121 , F05D2240/15 , Y02T50/676
摘要： A heat shield is provided for use in an inner cavity of a gas turbine engine component. The heat shield comprises a heat shield body comprising opposed side portions defining an inner channel. An inner section of a side portion of the opposed side portions is inwardly sloped such that a cross-section of the heat shield body is smaller in an inner body portion relative to a cross-section of an outer body portion thereof. An aperture is disposed through the side portion in a selected radial position. A vane assembly including the heat shield is also provided.
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公开(公告)号：US20170321572A1
公开(公告)日：2017-11-09
申请号：US15432177
申请日：2017-02-14
CPC分类号： F01D25/18 , F01D9/065 , F01D25/145 , F02C7/24 , F05D2220/32 , F05D2230/60 , F05D2240/15 , F05D2260/231
摘要： An apparatus and method of reducing operating temperatures of a gas turbine engine, exposed to a service tube assembly by utilizing a skirt and radially outer mount. The reduction in temperature exposure minimizes temperatures of the service tube during engine operation to reduce the incidence of oil coking or varnish.
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