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公开(公告)号：US11946412B2
公开(公告)日：2024-04-02
申请号：US16570923
申请日：2019-09-13
申请人： RTX Corporation
发明人： Gabriel L. Suciu , James D. Hill
CPC分类号： F02C3/14 , F01D25/24 , F01D25/30 , F02C3/04 , F02C3/10 , F02K3/00 , F02K3/04 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/60 , F05D2250/314 , Y02T50/60
摘要： A gas turbine engine includes a propulsor with a power turbine, a power turbine shaft extending forward therefrom defining a centerline axis, and a fan driven by the power turbine shaft. The fan is aligned with the centerline axis forward of the power turbine and is operatively connected to be driven by the power turbine through the power turbine shaft. A gas generator operatively connected to the propulsor is included downstream from the fan and forward of the power turbine, wherein the gas generator defines a generator axis offset from the centerline axis. The gas generator is operatively connected to the power turbine to supply combustion products for driving the power turbine.
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公开(公告)号：US20180371942A1
公开(公告)日：2018-12-27
申请号：US15632890
申请日：2017-06-26
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D5/085 , F05D2220/32 , F05D2240/61 , F05D2240/63 , F05D2250/14 , F05D2250/314 , F05D2260/20 , F05D2260/60 , F05D2260/941 , F16C3/02 , F16C37/00 , F16C2326/43 , F16C2360/23
摘要： A turbine shaft comprising: a tubular body having an outer surface and an inner surface opposite the outer surface, the inner surface defining a hollow chamber within the tubular body, wherein the tubular body includes a first longitudinal axis concentric to the tubular body; and one or more shielded elliptical orifices, at least one shielded elliptical orifice comprising: an elliptical orifice in the tubular body including a major axis extending from a first side to a second side of the elliptical orifice, wherein the major axis is oriented at an angle parallel with a torque field of the tubular body; a first shielding orifice in the tubular body having a first axis collinear to the major axis; and a second shielding orifice in the tubular body having a second axis collinear to the major axis, wherein the elliptical orifice is located in between the first and second shielding orifice.
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公开(公告)号：US20180238240A1
公开(公告)日：2018-08-23
申请号：US15913105
申请日：2018-03-06
CPC分类号： F02C7/28 , F02C3/04 , F02K1/805 , F05D2220/32 , F05D2240/55 , F05D2240/58 , F05D2250/14 , F05D2250/314 , F05D2250/34 , F05D2250/41 , F05D2260/38 , F05D2260/57 , F05D2300/603 , F05D2300/6034 , F16J15/3488 , Y02T50/672
摘要： A seal system is provided. The seal system may comprise a first duct having an annular geometry, a second duct overlapping the first duct in a radial direction, and a seal disposed between the first duct and the second duct. The seal may comprise a groove defined by the first duct and a piston configured to slideably engage the groove.
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公开(公告)号：US10036422B2
公开(公告)日：2018-07-31
申请号：US14395567
申请日：2013-03-06
申请人： BorgWarner Inc.
CPC分类号： F16C33/1085 , F01D25/168 , F02B39/14 , F05D2220/40 , F05D2240/52 , F05D2240/53 , F05D2250/192 , F05D2250/292 , F05D2250/314 , F05D2250/90 , F05D2260/98 , F16C17/04 , F16C17/042 , F16C17/047 , F16C33/1075 , F16C2360/24
摘要： An oil-lubricated, tapered-land thrust bearing assembly (60) for automotive turbochargers (10) including a thrust bearing (30). The thrust bearing (30) includes an assembly of a base (62) with at least one insert (64 or 66), which is designed to control the oil film as a purposefully compliant structure based on applied force to optimize performance at low and high power operation. The ramp angle is relatively large at a low load and decreases to a smaller ramp angle at higher loads. On one side of the turbocharger (10), the thrust bearing assembly (60) may operate with a flinger sleeve (34) and a thrust washer (24) within a complementary bearing housing cover (32).
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公开(公告)号：US10001032B2
公开(公告)日：2018-06-19
申请号：US14903371
申请日：2014-05-12
发明人： Ryo Takata , Soichiro Tabata
CPC分类号： F01D25/32 , F01D9/041 , F05D2220/31 , F05D2240/123 , F05D2250/182 , F05D2250/294 , F05D2250/312 , F05D2250/314
摘要： A hollow portion is formed inside a stator blade. A slit having an inlet opening on a pressure surface of the stator blade facing wet steam flow is formed that communicates with the hollow portion in the axial direction of the stator blade. The hollow portion communicates with a region having a lower pressure than the flow field of the wet steam flow. The pressure in the hollow portion is reduced to introduce water film flow formed from water drops on the pressure surface of the stator blade to the slit. The slit is formed at a downstream side end, in the flow direction of the wet steam flow, of the hollow portion, and the stator blade trailing edge side wall surface of the slit is at an acute angle to a leading edge side reference plane of the pressure side of the stator blade.
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公开(公告)号：US09989011B2
公开(公告)日：2018-06-05
申请号：US14639164
申请日：2015-03-05
CPC分类号： F02K3/04 , F01D13/003 , F01D13/006 , F02C3/06 , F02C7/36 , F02K1/52 , F02K3/025 , F02K3/06 , F05D2220/323 , F05D2250/314 , F05D2260/4031
摘要： A bypass housing receives a fan and defines a front end. An airflow path delivers air into an inlet duct over a limited circumferential extent of the bypass housing. An airflow path passes across a low pressure compressor rotor. An airflow path passes through a core engine, which includes a high pressure compressor rotor, a combustor, and a high pressure turbine rotor. Products of combustion downstream of the high pressure turbine rotor pass into an intermediate duct and then across a low pressure turbine rotor. The low pressure turbine rotor is positioned closer to the front end of the engine than is the high pressure turbine rotor. The low pressure turbine rotor is positioned axially intermediate the low pressure compressor rotor and the fan. The low pressure turbine rotor drives both the fan and the low pressure turbine rotor. An aircraft is also disclosed.
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公开(公告)号：US09957814B2
公开(公告)日：2018-05-01
申请号：US14827453
申请日：2015-08-17
发明人： Clifford J. Musto , Sasha M. Moore , Thomas N. Slavens , San Quach , Nicholas M. LoRicco , Timothy J. Jennings , John McBrien
CPC分类号： F01D5/187 , F01D5/186 , F01D9/023 , F01D9/041 , F01D9/065 , F01D11/08 , F02K1/822 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/11 , F05D2240/81 , F05D2250/314 , F05D2260/202 , F23R3/002 , F23R2900/03042 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine component includes a wall that provides an exterior surface and an interior flow path surface. A film cooling hole extends through the wall and is configured to fluidly connect the interior flow path surface to the exterior surface. The film cooling hole has a pocket that faces the interior flow path and extends substantially in a longitudinal direction. The film cooling hole has a portion downstream from the pocket and is arranged at an angle relative to the longitudinal direction and extends to the exterior surface.
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公开(公告)号：US09885482B1
公开(公告)日：2018-02-06
申请号：US15355665
申请日：2016-11-18
申请人： Siemens Energy, Inc.
发明人： David J. Wiebe
CPC分类号： F23R3/46 , F01D9/023 , F02C3/04 , F02C3/14 , F05D2230/80 , F05D2250/314 , Y10T29/49229
摘要： A method of making an aero-derivative gas turbine engine (100) is provided. A combustor outer casing (68) is removed from an existing aero gas turbine engine (60). An annular combustor (84) is removed from the existing aero gas turbine engine. A first row of turbine vanes (38) is removed from the existing aero gas turbine engine. A can annular combustor assembly (122) is installed within the existing aero gas turbine engine. The can annular combustor assembly is configured to accelerate and orient combustion gasses directly onto a first row of turbine blades of the existing aero gas turbine engine. A can annular combustor assembly outer casing (108) is installed to produce the aero-derivative gas turbine engine (100). The can annular combustor assembly is installed within an axial span (85) of the existing aero gas turbine engine vacated by the annular combustor and the first row of turbine vanes.
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公开(公告)号：US20180016928A1
公开(公告)日：2018-01-18
申请号：US15545819
申请日：2015-12-16
IPC分类号： F01D11/02 , F01D5/02 , F01D9/04 , F16J15/447
CPC分类号： F01D11/02 , F01D5/02 , F01D5/225 , F01D9/041 , F05D2220/31 , F05D2220/32 , F05D2240/127 , F05D2240/55 , F05D2250/314 , F05D2250/71 , F16J15/447 , F16J15/4472
摘要： A turbine is provided with a seal device. The seal device includes: at least one step surface disposed in a region of an outer peripheral surface of a rotor facing a shroud of a stationary vane in the radial direction of the rotor, the at least one step surface facing upstream in a flow direction of the fluid and dividing the region of the outer peripheral surface into at least two sections in an axial direction of the rotor: at least two seal fins protruding toward the at least two sections from the stationary vane and facing the at least two sections via a seal gap; and a swirling-component application portion disposed on an end side of the shroud of the stationary vane with respect to the axial direction of the rotor and configured to be capable of applying a swirling component to the fluid flowing toward the seal gap.
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公开(公告)号：US20170284205A1
公开(公告)日：2017-10-05
申请号：US15507071
申请日：2015-08-28
CPC分类号： F01D5/147 , B64C11/06 , B64C11/30 , B64D2027/005 , F01D1/26 , F01D5/06 , F01D7/00 , F02K3/072 , F05D2220/30 , F05D2220/325 , F05D2250/314 , F05D2260/74 , F05D2260/79 , F05D2260/961 , Y02T50/66 , Y02T50/673
摘要： A variable-pitch bladed disc including a plurality of blades, each at a variable pitch in relation to a rotation axis of the blade and each having a root, the plurality of blades including at least one first blade and at least one second blade, a plurality of rotor connecting shafts, each having a root and a tip, each root being mounted at the tip of a corresponding rotor connecting shaft by way of a pivot so as to allow each blade to rotate about the blade rotation axis, the first blade having a first blade inclination, such that the first blade is inclined in a fixed manner with respect to the blade rotation axis of the first blade, and the second blade having a second blade inclination different from the first blade inclination.
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