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公开(公告)号：US20190195132A1
公开(公告)日：2019-06-27
申请号：US16328743
申请日：2017-08-28
发明人： Gordon Tajiri , Michael Thomas Kenworthy , Yanzhe Yang , Dattu GV Jonnalagadda , Elizabeth Diane Turner
CPC分类号： F02C7/18 , F05D2260/213 , F05D2270/42 , F05D2300/505 , F28D1/0246 , F28D2021/0021 , F28D2021/0026 , F28F3/048 , F28F7/02 , F28F2255/02 , F28F2255/04 , F28F2280/10 , F28F2280/105 , Y02T50/672 , Y02T50/675
摘要： A fan casing assembly, connection assembly and method for moving a fan casing cooler. The fan casing assembly for the turbine engine can include an annular fan casing with a peripheral wall having a flow path defined through the casing. A fan casing cooler can mount along the peripheral wall in order to confront a cooling fluid flow within the flow path in order to cool a fluid through the fan casing cooler.
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公开(公告)号：US20190162118A1
公开(公告)日：2019-05-30
申请号：US16264837
申请日：2019-02-01
CPC分类号： F02C7/18 , B64D2013/0603 , F01D25/12 , F02C6/08 , F02C9/18 , F02K3/06 , F02K3/062 , F05D2220/324 , F05D2220/327 , F05D2250/51 , Y02T50/675
摘要： A gas turbine engine has a first source of air to be delivered into a core of the engine, and a second source of air, distinct from the first source of air and including separately controlled first and second fans, each delivering air into respective first and second conduits connected to distinct auxiliary applications.
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公开(公告)号：US20180328313A1
公开(公告)日：2018-11-15
申请号：US16036130
申请日：2018-07-16
IPC分类号： F02K1/82
CPC分类号： F02K1/822 , F05D2250/25 , F05D2260/30 , Y02T50/675 , Y10T29/49234
摘要： A method includes providing an exhaust liner as a first duct, providing a second duct having an opening therein, and spacing the first duct radially inward of the second duct. A spring connects the first and second ducts together and has first and second ends. A first mount comprises a first bracket portion associated with the spring and a second bracket portion directly fixed to the first duct. The first bracket portion is directly fixed to the first end of the spring and the second end of the spring is fixed to a second mount that comprises a casing plate having an area greater than the opening. The first end of the spring and the first bracket portion are inserted through the opening and the first bracket portion is attached to the second bracket portion. The casing plate is directly fixed to a radially outward facing surface of the second duct.
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公开(公告)号：US10125723B1
公开(公告)日：2018-11-13
申请号：US16036130
申请日：2018-07-16
CPC分类号： F02K1/822 , F05D2250/25 , F05D2260/30 , Y02T50/675 , Y10T29/49234
摘要： A method includes providing an exhaust liner as a first duct, providing a second duct having an opening therein, and spacing the first duct radially inward of the second duct. A spring connects the first and second ducts together and has first and second ends. A first mount comprises a first bracket portion associated with the spring and a second bracket portion directly fixed to the first duct. The first bracket portion is directly fixed to the first end of the spring and the second end of the spring is fixed to a second mount that comprises a casing plate having an area greater than the opening. The first end of the spring and the first bracket portion are inserted through the opening and the first bracket portion is attached to the second bracket portion. The casing plate is directly fixed to a radially outward facing surface of the second duct.
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5.发明申请公开(公告)号：US20180313542A1
公开(公告)日：2018-11-01
申请号：US15770573
申请日：2016-10-27
CPC分类号： F23R3/14 , F23R3/28 , Y02T50/675
摘要： To improve air/fuel mixing at low speed, the invention concerns an aerodynamic injection system (30) for a combustion chamber (8) of an aircraft turbine engine, the system comprising a central body (70) comprising a first air circulation space (72) and a swirler (74) allowing air to penetrate into the first air circulation space (72), the hollow body (70) also comprising a fuel circuit (92, 93, 82) arranged at least partially around the first space (72), the circuit comprising a second annular space (82) for a fuel film to circulate and fuel supply structures (92, 93) communicating with the second space (82), the spaces (72, 82) opening into a third air and fuel mixing space (86). According to the invention, the system comprises fuel injection openings (90) that bring the fuel circuit into communication with the first space (72).
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公开(公告)号：US20180306116A1
公开(公告)日：2018-10-25
申请号：US16017042
申请日：2018-06-25
CPC分类号： F02C7/185 , F02C6/08 , F02C7/143 , F02C9/18 , F05D2240/40 , F05D2260/20 , F05D2260/211 , Y02T50/675
摘要： A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath and a turbine section fluidly connected to the combustor via the primary flowpath. Also included is a cascading cooling system having a first inlet connected to a first compressor bleed, a second inlet connected to a second compressor bleed downstream of the first compressor bleed, and a third inlet connected to a third compressor bleed downstream of the second compressor bleed. The cascading cooling system includes at least one heat exchanger configured to incrementally generate cooling air for at least one of an aft compressor stage and a foremost turbine stage relative to fluid flow through the turbine section.
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公开(公告)号：US20180298817A1
公开(公告)日：2018-10-18
申请号：US15485944
申请日：2017-04-12
CPC分类号： F02C7/047 , F01D25/02 , F01D25/10 , F02C9/18 , F04D27/001 , F04D27/009 , F04D27/0292 , F05D2220/32 , F05D2260/81 , F05D2260/83 , Y02T50/675
摘要： A system includes a controller coupled to an inlet bleed heat system of a compressor. The controller is configured to detect an icing condition of an inlet portion of the compressor by determining a current compressor efficiency value of the compressor, a current compressor flow value of the compressor, or any combination thereof, comparing the current compressor efficiency value to a compressor efficiency model of the compressor, the current compressor flow value to a compressor flow model of the compressor, or any combination thereof, and providing an icing indication to the inlet bleed heat system if a first difference between the current compressor efficiency value and the compressor efficiency model is greater than a first threshold, a second difference between the current compressor flow value and the compressor flow model is greater than a second threshold, or any combination thereof.
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公开(公告)号：US20180283210A1
公开(公告)日：2018-10-04
申请号：US15471708
申请日：2017-03-28
CPC分类号： F01D25/12 , F01D11/003 , F01D25/28 , F05D2220/32 , F05D2240/60 , F05D2260/20 , F16J15/164 , F16J15/3404 , Y02T50/675
摘要： A sealing apparatus for rotational equipment includes an annular seal plate rotatable around an axis. The annular seal plate includes an annular seal land surface, an internal plenum, a plurality of inlet passages, a plurality of cooling passages and a plurality of outlet passages. The inlet passages are arranged about the axis. Each of the inlet passages extends into the annular seal plate to the internal plenum. The cooling passages are arranged about the axis. Each of the cooling passages extends into the annular seal plate from the annular seal land surface to the internal plenum. The outlet passages are arranged about the axis. Each of the outlet passages extends into the annular seal plate to the internal plenum. The outlet passages are arranged radially between the inlet passages and the cooling passages.
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9.发明授权公开(公告)号：US10082080B2
公开(公告)日：2018-09-25
申请号：US15120679
申请日：2015-02-19
发明人： Christian Vessot , Matthieu Leyko
CPC分类号： F02C7/14 , F02C7/04 , F02K3/06 , F04D29/329 , F05D2220/36 , F05D2240/30 , F05D2260/20 , F05D2260/40311 , F05D2260/98 , Y02T50/675
摘要： A forward fan rotor is disclosed with a hub of axis of rotation (X) and a cone mounted on the hub of the fan. The cone comprises an air bleed orifice which opens into an air duct of which a forward end portion passes through the fan rotor, said forward end portion comprising mechanical air entrainment means. The air bleed orifice has an annular shape and in that the cone is divided by said orifice into a front vertex portion and a rear frustoconical portion.A turbomachine forward axial spool equipped with such a fan rotor is also disclosed.
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公开(公告)号：US20180266264A1
公开(公告)日：2018-09-20
申请号：US15426354
申请日：2017-02-07
CPC分类号： F01D11/04 , F01D9/023 , F01D9/041 , F01D9/042 , F01D11/005 , F01D25/005 , F01D25/12 , F02C3/14 , F05D2220/32 , F05D2240/35 , F05D2260/20 , F05D2300/6033 , F23R3/002 , F23R3/50 , F23R3/60 , F23R2900/00018 , Y02T50/672 , Y02T50/673 , Y02T50/675
摘要： Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall defining an inner boundary of a flow path and a plurality of pockets therein, and a unitary outer wall defining an outer boundary of the flow path. The unitary outer wall includes combustor and turbine portions that are integrally formed as a single unitary structure. The flow path assembly further comprises a plurality of nozzle airfoils that each have an inner end radially opposite an outer end and define an internal cavity for receipt of a flow of cooling fluid. The inner end of each nozzle airfoil is received in one of the plurality of inner wall pockets and defines an outlet for the flow of cooling fluid to flow from the internal cavity to the pocket, which forms a fluid curtain to discourage fluid leakage from the flow path.
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