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61.发明申请公开(公告)号：US20180340434A1
公开(公告)日：2018-11-29
申请号：US15605341
申请日：2017-05-25
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Man-Chun TSE , Sid-Ali MESLIOUI
CPC classification number: F01D9/048 , F01D5/146 , F01D17/165 , F02C3/145 , F02C7/042 , F02C9/20 , F04D19/02 , F04D29/522 , F04D29/541 , F04D29/701 , F05D2240/122 , F05D2250/182 , F05D2250/51 , F05D2260/961
Abstract: The gas turbine has a plurality of inlet guide vanes each having a blade having a leading edge, a trailing edge, a span extending along the leading edge, and pivot members at opposite ends of the leading edge, and being pivotally mounted across the radial-to-axial intake via the pivot members, the pivot axis extending axially across a radial portion of the radial-to-axial intake. The plurality of inlet guide vanes include a plurality of first inlet guide vanes, and a plurality of second inlet guide vanes, the second inlet guide vanes having a trailing edge recess differing from the corresponding portion of the first inlet guide vanes. During operation, when the inlet guide vanes are pivoted past a given angle toward the tangential orientation, a radial flow of gas is allowed through the trailing edge recesses to avoid or impede vortex whistle.
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公开(公告)号：US20180320708A1
公开(公告)日：2018-11-08
申请号：US15588871
申请日：2017-05-08
Applicant: Solar Turbines Incorporated
Inventor： Kenneth Gregory Thomas
CPC classification number: F04D29/644 , F01D5/066 , F04D19/02 , F04D29/321 , F05D2250/13 , F05D2250/132 , F05D2260/36
Abstract: An axial compressor of a turbine engine includes a plurality of disk and spacer pairs oriented along a common axis of rotation. Each of a disk and a spacer of the disk and spacer pairs has a contacting face defining an engagement between the disk and the spacer. The contacting face of each of the disk and the spacer includes a recessed area. A pin has a stem received within the recessed area of the disk and a head received within the recessed area of the spacer. The head of the pin includes at least two flats corresponding to complementary surfaces of the recessed area of the spacer.
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公开(公告)号：US10052716B2
公开(公告)日：2018-08-21
申请号：US15410531
申请日：2017-01-19
Applicant: ROLLS-ROYCE plc
Inventor： James R Lloyd , Oliver Jones , Jamie Sismey , Luke Freeman
CPC classification number: B23K20/129 , B23K20/002 , B23K20/12 , B23K35/3046 , B23K35/3053 , B23K35/325 , B23K2101/001 , B23P15/006 , F01D5/028 , F01D5/063 , F04D19/02 , F04D29/321 , F04D29/644 , F05D2230/239 , F05D2230/25 , F05D2240/80
Abstract: A method for the manufacture of a blisk drum is described. Disc forging for inertia welding together are provided with sacrificial material whose shape and position is selectively provided such that, on completion of the inertia welding process, integral blades can be fashioned from the sacrificial material. Other components such as buckets and balancing lands may also be provided from the sacrificial material.
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64.发明申请公开(公告)号：US20180187690A1
公开(公告)日：2018-07-05
申请号：US15904890
申请日：2018-02-26
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Bruce David Reynolds , Nick Nolcheff
CPC classification number: F04D27/02 , F01D25/24 , F04D19/02 , F04D27/001 , F04D27/0261 , F04D29/321 , F04D29/526 , F04D29/685 , F05D2220/32 , F05D2230/00
Abstract: Multistage gas turbine engine (GTE) compressors having optimized stall enhancement feature (SEF) configurations are provided, as are methods for the production thereof. The multistage GTE compressor includes a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine. In one embodiment, the method includes the steps or processes of selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine, identifying one or more stall limiting rotors at each of the selected engine speeds, establishing an SEF configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors, and producing the multistage GTE compressor in accordance with the optimized SEF configuration.
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公开(公告)号：US10012239B2
公开(公告)日：2018-07-03
申请号：US15296757
申请日：2016-10-18
Applicant: General Electric Company
Inventor： Michael James Dutka , Antanu Sadhu , Nandakumar Aladahalli Rangaswamy
CPC classification number: F04D29/544 , F01D5/141 , F02C3/06 , F04D19/02 , F04D29/324 , F04D29/384 , F05D2220/32 , F05D2240/35 , F05D2250/74 , Y02T50/673
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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Patent Agency Ranking
公开(公告)号：US20180135524A1
公开(公告)日：2018-05-17
申请号：US15872158
申请日：2018-01-16
Applicant: United Technologies Corporation
Inventor： William G. Sheridan
CPC classification number: F02C7/36 , F01D5/06 , F01D9/041 , F01D25/162 , F01D25/18 , F01D25/20 , F02C3/04 , F02C3/06 , F02C3/062 , F02C3/107 , F02C7/06 , F02C7/16 , F02C7/32 , F02K3/06 , F04D19/02 , F04D29/325 , F05D2220/32 , F05D2220/36 , F05D2240/35 , F05D2260/4031 , F05D2260/40311 , F05D2260/98 , F16H1/28 , F16H1/48 , F16H57/0412 , F16H57/0486 , Y02T50/671
Abstract: A disclosed gas turbine engine includes a fan including a plurality of fan blades rotatable about an axis, a bypass duct, a compressor section and a bypass ratio greater than 10. A combustor in fluid communication with the compressor section and a fan drive turbine in communication with the combustor. A gear system provides a speed reduction between the fan drive turbine and the fan and transfer power input from the fan drive turbine to the fan at an efficiency greater than 98%.
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公开(公告)号：US20180106272A1
公开(公告)日：2018-04-19
申请号：US15296823
申请日：2016-10-18
Applicant: General Electric Company
Inventor： Michael James Dutka , Antanu Sadhu , Sharan Shanti , Sunil Rajagopal
CPC classification number: F04D29/544 , F02C3/06 , F04D19/02 , F04D29/324 , F04D29/384 , F05D2220/32 , F05D2240/35 , F05D2250/74
Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
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公开(公告)号：US20170342858A1
公开(公告)日：2017-11-30
申请号：US15664682
申请日：2017-07-31
Applicant: United Technologies Corporation
Inventor： Michael E. McCune , Jason Husband
IPC: F01D25/16 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/28 , F02C7/36 , F04D29/32 , F04D29/056 , F04D29/053 , F04D19/02 , F02K3/06 , F04D25/04 , F02C7/32
CPC classification number: F01D25/164 , F01D5/06 , F01D9/02 , F01D15/12 , F01D25/16 , F01D25/28 , F02C7/32 , F02C7/36 , F02K3/06 , F04D19/02 , F04D25/045 , F04D29/053 , F04D29/056 , F04D29/321 , F04D29/325 , F05D2220/32 , F05D2240/60 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y10T29/49321
Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades, a fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a ring gear defining a ring gear transverse stiffness, at least one journal bearing defining a journal bearing transverse stiffness, a gear mesh defining a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. The ring gear transverse stiffness is less than 20% of the gear mesh transverse stiffness and the journal bearing transverse stiffness is less than or equal to the gear mesh transverse stiffness.
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公开(公告)号：US20170320159A1
公开(公告)日：2017-11-09
申请号：US15410531
申请日：2017-01-19
Applicant: ROLLS-ROYCE plc
Inventor： James R. LLOYD , Oliver JONES , Jamie SISMEY , Luke FREEMAN
CPC classification number: B23K20/129 , B23K20/002 , B23K20/12 , B23K35/3046 , B23K35/3053 , B23K35/325 , B23K2101/001 , B23P15/006 , F01D5/028 , F01D5/063 , F04D19/02 , F04D29/321 , F04D29/644 , F05D2230/239 , F05D2230/25 , F05D2240/80
Abstract: A method for the manufacture of a blisk drum is described. Disc forging for inertia welding together are provided with sacrificial material whose shape and position is selectively provided such that, on completion of the inertia welding process, integral blades can be fashioned from the sacrificial material. Other components such as buckets and balancing lands may also be provided from the sacrificial material.
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公开(公告)号：US20170306970A1
公开(公告)日：2017-10-26
申请号：US15413677
申请日：2017-01-24
Inventor： Detang Zeng , Chunqing Tan , Qing Gao , Meiyuan Li , Yongjun Zhang , Haisheng Chen
CPC classification number: F04D27/001 , F01D17/06 , F04D19/02 , F05D2260/81 , G06F17/17
Abstract: The present disclosure provides an extrapolation method of low rotational speed characteristics of a compressor, which is suitable for acquisition the low rotational speed characteristics of a gas turbine on the ground or an aircraft engine, the extrapolation method takes into account an application condition of a similarity principle and specialties of the low rotational speed operation condition of the compressor, and comprises modifying exponents of the similarity principle to obtain the optimal exponents by an optimization algorithm, and applying a coefficient fitting method for a variable operating condition calculation of the gas turbine to the extrapolation of low rotational speed characteristic of the compressor to obtain the low rotational speed characteristic.
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