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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：US20230296114A1
公开(公告)日：2023-09-21
申请号：US18201875
申请日：2023-05-25
发明人： Bruce L. Morin , Detlef Korte
IPC分类号： F04D29/66 , F02C3/107 , F02K3/04 , G06F30/17 , F01D15/12 , F04D29/32 , F01D5/14 , F02C3/04 , F02K3/06 , F01D5/06 , F01D25/24 , F02C7/36 , F04D25/04 , F04D29/053
CPC分类号： F04D29/663 , F02C3/107 , F02K3/04 , G06F30/17 , F01D15/12 , F04D29/325 , F01D5/14 , F02C3/04 , F02K3/06 , F01D5/06 , F01D25/24 , F02C7/36 , F04D25/045 , F04D29/053 , F04D29/321 , F05D2260/40311 , F05D2260/96 , F05D2270/304 , F05D2270/333 , F05D2230/50 , F05D2220/323
摘要： An aircraft system includes, among other things, an aircraft and a gas turbine engine coupled to the aircraft. The gas turbine engine includes a propulsor section including a propulsor, a compressor section, a turbine section including a first turbine and a second turbine, and a gear reduction between the propulsor and the second turbine. The second turbine includes a number of turbine blades in each of a plurality of rows of the second turbine. The second turbine blades operating at least some of the time at a rotational speed. The number of blades and the rotational speed being such that the following formula holds true for a majority of the blade rows of the second turbine: 5500 Hz≤(number of blades×speed)/60 sec≤10000 Hz. The gas turbine engine is rated to produce 15,000 pounds of thrust or more.
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公开(公告)号：US12123432B2
公开(公告)日：2024-10-22
申请号：US18201875
申请日：2023-05-25
发明人： Bruce L. Morin , Detlef Korte
IPC分类号： F02C7/36 , F01D5/06 , F01D5/14 , F01D15/12 , F01D25/24 , F02C3/04 , F02C3/107 , F02K3/04 , F02K3/06 , F04D25/04 , F04D29/053 , F04D29/32 , F04D29/66 , G06F30/17
CPC分类号： F04D29/663 , F01D5/06 , F01D5/14 , F01D15/12 , F01D25/24 , F02C3/04 , F02C3/107 , F02C7/36 , F02K3/04 , F02K3/06 , F04D25/045 , F04D29/053 , F04D29/321 , F04D29/325 , G06F30/17 , F05D2220/323 , F05D2230/50 , F05D2260/40311 , F05D2260/96 , F05D2270/304 , F05D2270/333
摘要： An aircraft system includes, among other things, an aircraft and a gas turbine engine coupled to the aircraft. The gas turbine engine includes a propulsor section including a propulsor, a compressor section, a turbine section including a first turbine and a second turbine, and a gear reduction between the propulsor and the second turbine. The second turbine includes a number of turbine blades in each of a plurality of rows of the second turbine. The second turbine blades operating at least some of the time at a rotational speed. The number of blades and the rotational speed being such that the following formula holds true for a majority of the blade rows of the second turbine: 5500 Hz≤(number of blades×speed)/60 sec≤10000 Hz. The gas turbine engine is rated to produce 15,000 pounds of thrust or more.
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公开(公告)号：US20230258088A1
公开(公告)日：2023-08-17
申请号：US18166504
申请日：2023-02-09
申请人： MTU Aero Engines AG
CPC分类号： F01D5/141 , F01D9/041 , F05D2240/122 , F05D2240/121 , F05D2240/80 , F05D2250/38 , F05D2250/71
摘要： A stator vane for a turbomachine, including an airfoil having a leading edge and a trailing edge, which are interconnected by a suction side and a pressure side, the airfoil extending substantially in a radial direction between an inner platform and an outer platform, wherein, when viewed in an axial direction of the turbomachine toward the trailing edge, the trailing edge extends so as to be inclined at a first angle to the pressure side radially on an outside in relation to the radial direction at a circumferential position at which the trailing edge meets the outer platform, and wherein the first angle between the trailing edge and a tangent to the outer platform at a transition from the outer platform to the trailing edge is between 72° and 84°.
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公开(公告)号：US20200173370A1
公开(公告)日：2020-06-04
申请号：US16667326
申请日：2019-10-29
发明人： David A. Topol , Bruce L. Morin , Detlef Korte
摘要： A gas turbine engine has a fan section including a fan, a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, and a gear reduction. The low pressure compressor and the low pressure turbine have a number of blades in each of at least one of a plurality of blade rows. The blades are rotatable at least some of the time at a rotational speed in operation. The number of blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor turbine: (number of blades×rotational speed)/60s≥5500 Hz, and the rotational speed is in revolutions per minute.
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公开(公告)号：US20160025004A1
公开(公告)日：2016-01-28
申请号：US14795911
申请日：2015-07-10
发明人： Bruce L. Morin , Detlef Korte
CPC分类号： F02C3/107 , F02K3/04 , F05D2220/32 , F05D2260/40311 , F05D2260/96
摘要： A gas turbine engine comprises a fan, a compressor section including a compressor having a low pressure portion and a high pressure portion, a combustor section, and a turbine having a downstream portion. A gear reduction effects a reduction in the speed of the fan relative to an input speed to the fan. The downstream portion of the turbine has a number of turbine blades in each of a plurality of rows of the downstream turbine portion. The turbine blades operate at least some of the time at a rotational speed. The number of blades and the rotational speed are such that the following formula holds true for at least one of the blade rows of the downstream turbine: (number of blades×speed)/60≧5500. The rotational speed is an approach speed in revolutions per minute. A method of designing a gas turbine engine and a turbine module are also disclosed.
摘要翻译： 燃气涡轮发动机包括风扇，包括具有低压部分和高压部分的压缩机的压缩机部分，燃烧器部分和具有下游部分的涡轮机。 齿轮减速可以降低风扇相对于风扇输入速度的速度。 涡轮机的下游部分在下游涡轮部分的多排中的每一排中具有多个涡轮机叶片。 涡轮叶片在转速下至少部分时间运转。 叶片的数量和转速使得对于下游涡轮机的至少一个叶片排，以下公式成立：（叶片数×速度）/60≥5500。 旋转速度是每分钟转数的接近速度。 还公开了一种设计燃气涡轮发动机和涡轮模块的方法。
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公开(公告)号：US20150204238A1
公开(公告)日：2015-07-23
申请号：US14248386
申请日：2014-04-09
发明人： Bruce L. Morin , Detlef Korte
CPC分类号： F02C3/113 , F02K3/04 , F05D2220/32 , F05D2260/40311 , F05D2260/96 , F16H1/28 , G06F17/5086 , Y02T50/671
摘要： A gas turbine engine includes a fan, a turbine having a fan drive rotor, and a speed reduction device effecting a reduction in the speed of the fan relative to an input speed from the fan drive rotor. The fan drive rotor has a number of turbine blades in at least one of a plurality of rows of the fan drive rotor, and the turbine blades operating at least some of the time at a rotational speed, and the number of turbine blades in the at least one row and the rotational speed being such that the following formula holds true for the at least one row of the fan drive turbine (the number of blades×the rotational speed)/(60 seconds/minute)>4000 Hz. The rotational speed being in revolutions per minute. A method is also disclosed.
摘要翻译： 燃气涡轮发动机包括风扇，具有风扇驱动转子的涡轮机和相对于来自风扇驱动转子的输入速度降低风扇速度的减速装置。 风扇驱动转子在风扇驱动转子的多行中的至少一行中具有多个涡轮叶片，并且涡轮叶片以至少一些时间在转速下运行，并且涡轮叶片的数量在 至少一排，并且转速使得对于风扇驱动涡轮机的至少一排（叶片数×转速）/（60秒/分钟）> 4000Hz，以下公式成立。 转速为每分钟转。 还公开了一种方法。
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公开(公告)号：US11220911B2
公开(公告)日：2022-01-11
申请号：US16278263
申请日：2019-02-18
申请人： MTU Aero Engines AG
摘要： A guide vane airfoil for placement in a flow path portion of a turbomachine is provided, which, relative to a flow pattern in flow path portion, has a leading edge and, downstream thereof, a trailing edge, as well as a suction side and a pressure side; relative to a longitudinal axis of the turbomachine, viewed in the axial direction, in a radially inner portion, forming a first angle α with a circular arc about the longitudinal axis, and, in a radially outer portion, a second angle γ with a circular arc about the longitudinal axis. The guide vane airfoil is inclined in the outer portion, thus γ−90°, in terms of absolute value, being >0° (|γ−90°|>0°), and the guide vane airfoil being more highly inclined in the outer portion than in the inner portion, thus γ−90°, in terms of absolute value, being >α−90° (|γ−90°|>α−90°).
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公开(公告)号：US20170122218A1
公开(公告)日：2017-05-04
申请号：US15404490
申请日：2017-01-12
发明人： David A. Topol , Bruce L. Morin , Detlef Korte
CPC分类号： G01P3/48 , F01D5/02 , F01D5/12 , F02C3/04 , F02C3/10 , F02C7/24 , F02C7/32 , F02C7/36 , F02K3/06 , F05D2200/13 , F05D2200/14 , F05D2220/32 , F05D2220/36 , F05D2260/40311 , F05D2260/96 , Y02T50/673 , Y10T29/49236 , Y10T29/4932
摘要： A gas turbine engine has a fan, a turbine section having a first turbine including a first turbine, a compressor, and a gear reduction positioned between the fan and the first turbine. Each of the compressor and the first turbine includes a number of blades in each of a plurality of blade rows, the number of blades rotatable at least some of the time at a rotational speed in operation, and the number of blades and the rotational speed being such that the following formula holds true for the plurality of the blade rows of the first turbine, but does not hold true for any of the blade rows of the compressor rotor: (number of blades×rotational speed)/60≧5500, and the rotational speed being an approach speed in revolutions per minute.
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公开(公告)号：US20160130949A1
公开(公告)日：2016-05-12
申请号：US14996544
申请日：2016-01-15
发明人： Bruce L. Morin , Detlef Korte
CPC分类号： F04D29/663 , F01D5/06 , F01D5/14 , F01D15/12 , F01D25/24 , F02C3/04 , F02C3/107 , F02C7/36 , F02K3/04 , F02K3/06 , F04D25/045 , F04D29/053 , F04D29/321 , F04D29/325 , F05D2220/323 , F05D2230/50 , F05D2260/40311 , F05D2260/96 , F05D2270/304 , F05D2270/333 , G06F17/5086
摘要： A turbine module according to an example of the present disclosure includes, among other things, a fan drive rotor having a plurality of blade rows each including a number of blades. A majority of the blade rows are capable of rotating at a rotational speed, so that when measuring the rotational speed in revolutions per minute: (number of blades×the rotational speed)/60≧about 5500 Hz.
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