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公开(公告)号：US20180016987A1
公开(公告)日：2018-01-18
申请号：US15553207
申请日：2015-03-10
发明人： Graham Frank Howarth , Andrew Michael Roach , Steven Thomas Davies , Richard David Cedar , Michael Moses Martinez , Timothy Richard DePuy
IPC分类号： F02C7/24
CPC分类号： F02C7/24 , F02C7/045 , F02K1/827 , F05D2220/323 , F05D2250/11 , F05D2250/14 , F05D2250/283 , F05D2260/963 , G10K11/172 , Y02T50/672
摘要： An acoustic liner for a turbine engine, the acoustic liner includes a support layer that includes a set of partitioned cavities with open faces, a facing sheet operably coupled to the support layer such that the facing sheet overlies and closes the open faces, a set of perforations located in the facing sheet and in fluid communication with a corresponding one of the cavities to form a set of acoustic resonators, and at least a subset of the perforations have an axially-oriented, relative to the axial flow path, inlet.
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公开(公告)号：US20240003543A1
公开(公告)日：2024-01-04
申请号：US17853200
申请日：2022-06-29
发明人： Ravikanth Avancha , Ravish Karve , Jeffrey Donald Clements , Hiranya Kumar Nath , Timothy Richard DePuy
CPC分类号： F02C7/24 , F23R3/002 , F23R2900/00014
摘要： A gas turbine engine is provided. The gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order and together defining a working gas flowpath, the turbomachine including an acoustic liner, the acoustic liner having: a flowpath wall exposed to the working gas flowpath, the flowpath wall defining an opening; and a duct wall extending from the flowpath wall defining at least in part an acoustic passage defining a volume, the acoustic passage operable to attenuate noise through the working gas flowpath during an operating condition of the gas turbine engine.
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公开(公告)号：US20230043809A1
公开(公告)日：2023-02-09
申请号：US17388618
申请日：2021-07-29
发明人： Scott Alan Schimmels , Jeffrey Douglas Rambo , Daniel Alan Niergarth , Daniel Lawrence Tweedt , Michael Simonetti , Michael Julian Castillo , Timothy Richard DePuy , Steven Benjamin Morris
摘要： A gas turbine engine is provided including a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order; a rotor assembly driven by the turbomachine, the rotor assembly, the turbomachine, or both comprising a substantially annular duct relative to the centerline of the gas turbine engine, the annular duct defining a flowpath; a heat exchanger positioned within the annular duct and extending substantially continuously along the circumferential direction, the heat exchanger comprising a first material defining a heat exchange surface exposed to the flowpath, wherein the first material defines a heat exchange coefficient and wherein the heat exchange surface defines a surface area (A), and wherein the heat exchanger has an effective transmission loss (ETL) of between 5 decibels and 1 decibel for an operating condition.
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公开(公告)号：US12012898B2
公开(公告)日：2024-06-18
申请号：US17979992
申请日：2022-11-03
发明人： Brandon Wayne Miller , Egbert Geertsema , Arthur W. Sibbach , Andrew Hudecki , Timothy Richard DePuy , John C. Schilling , Frank Worthoff , Tsuguji Nakano
CPC分类号： F02C7/24 , F02C7/36 , F05D2260/96
摘要： A gas turbine engine comprises a fan, a core turbine engine coupled to the fan, a fan case housing the fan and the core turbine engine, a plurality of outlet guide vanes extending between the core turbine engine and the fan case, and an acoustic spacing. The fan comprises a plurality of fan blades that define a fan diameter and a BEAL. The fan case comprises an inlet and an inlet length between the inlet and the fan. The acoustic spacing comprises a distance between the fan and the plurality of outlet guide vanes, and in combination with the BEAL determines an acoustic spacing ratio of the gas turbine engine.
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公开(公告)号：US20230322382A1
公开(公告)日：2023-10-12
申请号：US17658909
申请日：2022-04-12
CPC分类号： B64C39/10 , B64D33/02 , B64C2039/105 , B64D2033/0206
摘要： A blended wing body aircraft includes a body section having an aerodynamic lifting surface. The body section includes an upper body and a lower body. The blended wing body aircraft also includes a plurality of blended wing sections further defining the body section. The blended wing body aircraft includes one or more grooves in the body section. The one or more grooves extend from the upper body towards the lower body. The blended wing body aircraft further includes one or more open-fan engines mounted at least partially within the one or more grooves. The one or more open-fan engines ingest a portion of a boundary layer of the blended wing body aircraft.
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公开(公告)号：US20220259985A1
公开(公告)日：2022-08-18
申请号：US17176106
申请日：2021-02-15
摘要： A turbomachinery engine includes an unducted rotor assembly, a low-pressure turbine, a low-pressure shaft, a gearbox, and an engine correlation parameter. The unducted rotor assembly includes a plurality of rotor blades arranged in a single row and defining a blade diameter. The gearbox includes an input, an output, and a gear ratio. The input of the gearbox is coupled to the low-pressure shaft (which is coupled to the LPT), and the output of the gearbox is coupled to the unducted rotor assembly. The engine correlation parameter is greater than 0.17 and less than 0.83. The engine correlation parameter equals D/N/GR, where D is the blade tip diameter measured in feet, N is the stage count of the low-pressure turbine, and GR is the gear ratio of the gearbox. The unducted propulsor assembly optionally includes a disk loading within a range of 60-180 HP/ft2 at a takeoff flight condition.
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公开(公告)号：US20240151185A1
公开(公告)日：2024-05-09
申请号：US17979992
申请日：2022-11-03
发明人： Brandon Wayne Miller , Egbert Geertsema , Arthur W. Sibbach , Andrew Hudecki , Timothy Richard DePuy , John C. Schilling , Frank Worthoff , Tsuguji Nakano
CPC分类号： F02C7/24 , F02C7/36 , F05D2260/96
摘要： A gas turbine engine comprises a fan, a core turbine engine coupled to the fan, a fan case housing the fan and the core turbine engine, a plurality of outlet guide vanes extending between the core turbine engine and the fan case, and an acoustic spacing. The fan comprises a plurality of fan blades that define a fan diameter and a BEAL. The fan case comprises an inlet and an inlet length between the inlet and the fan. The acoustic spacing comprises a distance between the fan and the plurality of outlet guide vanes, and in combination with the BEAL determines an acoustic spacing ratio of the gas turbine engine.
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公开(公告)号：US11927134B1
公开(公告)日：2024-03-12
申请号：US18160375
申请日：2023-01-27
CPC分类号： F02C7/12 , F01D25/12 , F01D25/14 , F05D2220/323 , F05D2240/14 , F05D2260/213
摘要： A gas turbine engine is provided, having a turbomachine and a rotor assembly driven by the turbomachine and operable at a first blade passing frequency (f1) greater than or equal to 2,500 hertz and less than or equal to 5,000 hertz during a high power operating condition; a heat exchanger positioned within an annular duct and extending substantially continuously along the circumferential direction, wherein an effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for a high power operating condition, and wherein the heat exchanger comprises a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the high power operating condition, the OARR equal to:
sin
(
2
×
π
×
f
1
a
1
×
L
i
)
2
wherein a1 is equal to 13,200 inches per second during the high power operating condition.-
公开(公告)号：US20240052780A1
公开(公告)日：2024-02-15
申请号：US17819426
申请日：2022-08-12
CPC分类号： F02C7/045 , F01D25/04 , F05D2220/32 , F05D2260/96
摘要： An inlet duct for a nacelle of a ducted fan engine includes an inlet portion at an upstream end of the inlet duct, an acoustic liner arranged downstream of the inlet portion, and a fan section arranged downstream of the acoustic liner. The inlet portion and the acoustic liner are coupled together at an inlet-acoustic liner interface extending circumferentially about the inner surface of the inlet duct, and the acoustic liner and the fan section are coupled together at a fan section hardwall-acoustic liner interface extending circumferentially about the inner surface of the inlet duct. At least one of the acoustic liner, the inlet-acoustic liner interface, and the fan section hardwall-acoustic liner interface having a structure that circumferentially alters a magnitude and a phase of an acoustic wave reflection of the inlet duct to attenuate flutter bite of a fan.
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公开(公告)号：US20240051673A1
公开(公告)日：2024-02-15
申请号：US17887872
申请日：2022-08-15
发明人： Kishore Ramakrishnan , Trevor Howard Wood , Harry Kirk Mathews, JR. , Eric Richard Westervelt , Honggang Wang , Timothy Richard DePuy
CPC分类号： B64D31/06 , B64D27/10 , B64D27/24 , B64D2027/026
摘要： An aircraft engine includes a low pressure spool, a high pressure spool, and an alternative power source. The alternative power source is configured to add power to the high pressure spool. A controller is configured to determine a noise sensitive condition; and control, in response to determining the noise sensitive condition, the alternative power source to add power to the high pressure spool.
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