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公开(公告)号：US20220010732A1
公开(公告)日：2022-01-13
申请号：US17488690
申请日：2021-09-29
发明人： Bruce L. Morin , David A. Topol , Detlef Korte
IPC分类号： F02C7/24 , F02K3/06 , F01D5/02 , F01D5/12 , F01D9/04 , F01D15/12 , F01D17/10 , F01D5/16 , F01D25/04 , F02C3/107 , F02C7/36
摘要： A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section, a geared architecture, a high spool and a low spool. The high spool includes a high pressure compressor and a high pressure turbine. The low spool includes a low pressure compressor and a low pressure turbine. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is greater than or equal to 0.5 at an approach speed.
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公开(公告)号：US11118507B2
公开(公告)日：2021-09-14
申请号：US16867668
申请日：2020-05-06
摘要： A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.
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公开(公告)号：US20230151741A1
公开(公告)日：2023-05-18
申请号：US17701010
申请日：2022-03-22
发明人： Anthony R. Bifulco , David A. Topol
CPC分类号： F01D25/24 , F01D25/28 , F01D9/041 , F05D2240/14 , F05D2250/11 , F05D2260/30 , F05D2260/606 , F05D2260/96
摘要： A gas turbine engine includes a fan rotor driven by a fan drive turbine about an axis through a gear reduction to reduce a speed of the fan rotor relative to a speed of the fan drive turbine. A fan case surrounds the fan rotor, and a core engine with a compressor section, including a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection is between the fan case and the core engine includes three triangular-frame connecting members rigidly connected to the fan case at a fan case connection point, and to the core engine at a core engine connection point. The triangular-frame connecting members each are defined by two rigid legs which extend between the fan case and to the core engine, along directions each have a component extending radially inwardly and a component in opposed circumferential directions to each other. A plurality of non-structural fan exit guide vanes and the non-structural fan exit guide vanes are provided with an acoustic feature to reduce noise. The non-structural fan exit guide vanes are rigidly mounted to at least one of the fan case and the core engine.
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公开(公告)号：US20230127925A1
公开(公告)日：2023-04-27
申请号：US18088196
申请日：2022-12-23
发明人： Anthony R. Bifulco , David A. Topol
摘要： A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A fan case surrounds the fan rotor. A core engine has a compressor section and includes a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of aft connecting members rigidly connected to the fan case, and to the core engine. A plurality of fan exit guide vanes are rigidly connected to the fan case, with the fan exit guide vanes including structural fan exit guide vanes which are rigidly connected to the core engine, and non-structural fan exit guide vanes, and the non-structural fan exit guide vanes being provided with an acoustic feature to reduce noise.
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公开(公告)号：US20210277829A1
公开(公告)日：2021-09-09
申请号：US16863218
申请日：2020-04-30
发明人： Daniel K. Van Ness , Anthony R. Bifulco , David A. Topol , David A. Knaul , Michael Raymond LaFavor
摘要： Disclosed is an acoustic liner for a gas turbine engine, having: a face sheet; a first plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the first plurality of resonator chamber cavities defining a first aggregated volume that is configured to target noise attenuation at a first frequency, the first plurality of resonator chamber cavities include first and second resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other; and a second plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the second plurality of resonator chamber cavities define a second aggregated volume that differs from the first aggregated volume and is configured to target noise attenuation at a second frequency, the second plurality of resonator chamber cavities include third and fourth resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other.
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公开(公告)号：US11927106B2
公开(公告)日：2024-03-12
申请号：US18088196
申请日：2022-12-23
发明人： Anthony R. Bifulco , David A. Topol
CPC分类号： F01D25/28 , F01D9/06 , F01D25/24 , F05D2240/14 , F05D2250/191 , F05D2260/30 , F05D2260/606 , F05D2260/96
摘要： A gear reduction reduces a speed of a fan rotor relative to a speed of a fan drive turbine. A fan case surrounds the fan rotor. A core engine has a compressor section and includes a low pressure compressor. The fan rotor delivers air into a bypass duct defined between the fan case and the core engine. A rigid connection between the fan case and the core engine includes a plurality of aft connecting members rigidly connected to the fan case, and to the core engine. A plurality of fan exit guide vanes are rigidly connected to the fan case, with the fan exit guide vanes including structural fan exit guide vanes which are rigidly connected to the core engine, and non-structural fan exit guide vanes, and the non-structural fan exit guide vanes being provided with an acoustic feature to reduce noise.
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公开(公告)号：US11719161B2
公开(公告)日：2023-08-08
申请号：US17488690
申请日：2021-09-29
发明人： Bruce L. Morin , David A. Topol , Detlef Korte
IPC分类号： F01D5/02 , F02C7/24 , F02K3/06 , F01D5/12 , F01D9/04 , F01D15/12 , F01D17/10 , F01D5/16 , F01D25/04 , F02C3/107 , F02C7/36
CPC分类号： F02C7/24 , F01D5/02 , F01D5/12 , F01D5/16 , F01D9/041 , F01D15/12 , F01D17/105 , F01D25/04 , F02C3/107 , F02C7/36 , F02K3/06 , F05D2200/36 , F05D2210/31 , F05D2220/32 , F05D2220/327 , F05D2240/301 , F05D2240/307 , F05D2260/40311 , F05D2260/96 , Y02T50/60
摘要： A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section, a geared architecture, a high spool and a low spool. The high spool includes a high pressure compressor and a high pressure turbine. The low spool includes a low pressure compressor and a low pressure turbine. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is greater than or equal to 0.5 at an approach speed.
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公开(公告)号：US11560849B2
公开(公告)日：2023-01-24
申请号：US17503814
申请日：2021-10-18
发明人： Bruce L. Morin , David A. Topol , Detlef Korte
IPC分类号： F02C7/24 , F02K3/06 , F01D5/02 , F01D5/12 , F01D9/04 , F01D15/12 , F01D17/10 , F01D5/16 , F01D25/04 , F02C3/107 , F02C7/36
摘要： A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a propulsor section including a propulsor, a turbine section including a first turbine and a second turbine, a compressor section driven by the turbine section, the compressor section including a first compressor and a second compressor, and a geared architecture driven by the first turbine. The propulsor is driven by the first turbine via the geared architecture. At least one stage of the turbine section includes an array of rotatable blades and an array of vanes. A ratio of the number of vanes to the number blades is greater than or equal to 1.55. A mechanical tip rotational Mach number of the blades is configured to be greater than or equal to 0.5 at an approach speed.
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公开(公告)号：US11339720B2
公开(公告)日：2022-05-24
申请号：US16863218
申请日：2020-04-30
发明人： Daniel K. Van Ness , Anthony R. Bifulco , David A. Topol , David A. Knaul , Michael Raymond LaFavor
摘要： Disclosed is an acoustic liner for a gas turbine engine, having: a face sheet; a first plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the first plurality of resonator chamber cavities defining a first aggregated volume that is configured to target noise attenuation at a first frequency, the first plurality of resonator chamber cavities include first and second resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other; and a second plurality of resonator chamber cavities, distributed non-uniformly against the face sheet, the second plurality of resonator chamber cavities define a second aggregated volume that differs from the first aggregated volume and is configured to target noise attenuation at a second frequency, the second plurality of resonator chamber cavities include third and fourth resonator chamber cavities fluidly coupled to each other, which have different configurations with respect to each other.
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公开(公告)号：US20210372323A1
公开(公告)日：2021-12-02
申请号：US17399309
申请日：2021-08-11
摘要： A fan section for a gas turbine engine according to an example of the present disclosure includes, among other things, a fan rotor having fan blades, and a plurality of fan exit guide vanes positioned downstream of the fan rotor. The fan rotor is configured to be driven through a gear reduction. A ratio of a number of fan exit guide vanes to a number of fan blades is defined. The fan exit guide vanes are provided with optimized sweep and optimized lean.
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