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公开(公告)号：US11078805B2
公开(公告)日：2021-08-03
申请号：US16384076
申请日：2019-04-15
Applicant: United Technologies Corporation
Inventor： Michael M. Joly , Simon W. Evans , Dilip Prasad , Gorazd Medic , Georgi Kalitzin , Dmytro Mykolayovych Voytovych
Abstract: A compressor for use in a gas turbine engine including: an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine; a casing, the casing including a radially inward surface; and a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and wherein the forward groove wall is operably shaped to generate an aft directed jet.
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公开(公告)号：US20210025335A1
公开(公告)日：2021-01-28
申请号：US16521633
申请日：2019-07-25
Applicant: United Technologies Corporation
Inventor： Neil Terwilliger , Dilip Prasad
Abstract: A method of operating a turbofan engine includes coupling an electric motor to drive a fan rotatable within a nacelle, detecting an in-flight operating condition indicative of an increase in drag, and driving rotation of the fan with the electric motor to redirect a flow of air through the nacelle to reduce drag. A turbofan engine is also disclosed.
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公开(公告)号：US10233948B2
公开(公告)日：2019-03-19
申请号：US14768839
申请日：2013-12-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David A. Topol , Dilip Prasad
Abstract: In accordance with one aspect of the disclosure, a rotor for a gas turbine engine is disclosed. The rotor may include a rotor disk and a plurality of blade extending radially outward from the rotor disk. At least one of the blades may have a physical nonuniformity. The blades may be distributed about the rotor disk based on any physical nonuniformities of the blades to generate at least one decay-resistant harmonic.
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公开(公告)号：US20180202362A1
公开(公告)日：2018-07-19
申请号：US15407586
申请日：2017-01-17
Applicant: United Technologies Corporation
Inventor： Matthew E. Bintz , Dilip Prasad
CPC classification number: F02C7/185 , F01D5/081 , F01D25/12 , F02C6/08 , F02C7/18 , F04D27/0207 , F05D2260/205 , F05D2260/207 , F05D2260/212 , F05D2260/232 , F05D2260/601 , Y02T50/675
Abstract: A gas turbine engine includes an engine core having a compressor section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor section. At least one compressor bleed connects a compressor flowpath with a first cooled cooling air path. The first cooled cooling air path includes a supplementary coolant injector connected to a supplementary coolant supply. The cooled cooling air path including a portion exterior to the engine core.
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公开(公告)号：US20200332673A1
公开(公告)日：2020-10-22
申请号：US16388199
申请日：2019-04-18
Applicant: United Technologies Corporation
Inventor： Michael M. Joly , Andrzej Ernest Kuczek , Zaffir A. Chaudhry , Gorazd Medic , Dilip Prasad
Abstract: A gas turbine engine includes a plurality of blades circumferentially spaced from each other. A plurality of rings are spaced radially outward from the plurality of blade. At least one actuator is in mechanical communication with the plurality of rings for moving the plurality of rings in an axial direction to create an axial gap adjacent at least one of the plurality of rings.
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Patent Agency Ranking
公开(公告)号：US20160003264A1
公开(公告)日：2016-01-07
申请号：US14768839
申请日：2013-12-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： David A. Topol , Dilip Prasad
CPC classification number: F04D29/666 , F01D5/06 , F01D5/10 , F01D5/145 , F04D29/321 , F05D2220/36 , F05D2260/961 , Y02T50/671 , Y02T50/673
Abstract: In accordance with one aspect of the disclosure, a rotor for a gas turbine engine is disclosed. The rotor may include a rotor disk and a plurality of blade extending radially outward from the rotor disk. At least one of the blades may have a physical nonuniformity. The blades may be distributed about the rotor disk based on any physical nonuniformities of the blades to generate at least one decay-resistant harmonic.
Abstract translation: 根据本公开的一个方面，公开了一种用于燃气涡轮发动机的转子。 转子可以包括转子盘和从转子盘径向向外延伸的多个叶片。 至少一个叶片可能具有物理不均匀性。 叶片可以基于叶片的任何物理不均匀性而围绕转子盘分布以产生至少一个抗衰减谐波。
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公开(公告)号：US20140311149A1
公开(公告)日：2014-10-23
申请号：US13664647
申请日：2012-10-31
Applicant: United Technologies Corporation
Inventor： Sue-Li Chuang , Yuan Dong , Sanjay S. Hingorani , Dilip Prasad
IPC: F04D29/38
CPC classification number: F04D29/384 , F01D5/141 , F05D2220/36 , F05D2250/74 , Y02T50/672 , Y02T50/673 , Y10T137/0536 , Y10T137/0645
Abstract: A fan blade for a gas turbine engine includes an airfoil that includes leading and trailing edges joined by pressure and suction sides to provide an exterior airfoil surface that extends in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1. The Cartesian coordinates are provided by an axial coordinate scaled by a local axial chord. A circumferential coordinate is scaled by the local axial chord, and a span location. The local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
Abstract translation: 用于燃气涡轮发动机的风扇叶片包括翼型件，其包括通过压力和吸力侧连接的前缘和后缘，以提供沿径向方向延伸到尖端的外部翼面。 外部翼面表面基本上符合由表1中所示的一组笛卡尔坐标所描述的翼型的多个横截面轮廓。笛卡尔坐标由通过局部轴向弦缩放的轴向坐标提供。 圆周坐标由局部轴向弦和跨度位置缩放。 局部轴向弦对应于跨距处的前缘和后缘之间的翼型的宽度。
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公开(公告)号：US11255214B2
公开(公告)日：2022-02-22
申请号：US16672938
申请日：2019-11-04
Applicant: United Technologies Corporation
Inventor： Dilip Prasad , Gavin Hendricks
Abstract: A compressor with negative coefficient of thermal expansion case material comprising a rotor having blades with tips, the case including an inner case comprising a negative coefficient of thermal expansion material, and a tip clearance located between the tips and the inner case; wherein the tip clearance is maintained responsive to a flow of air over the negative coefficient of thermal expansion material.
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公开(公告)号：US11136895B2
公开(公告)日：2021-10-05
申请号：US16268683
申请日：2019-02-06
Applicant: United Technologies Corporation
Inventor： Georgi Kalitzin , Gorazd Medic , Om P. Sharma , Junsok Yi , Dilip Prasad
Abstract: A casing treatment comprising a hub having a surface, the hub being rotatable about an axis within a casing of a gas turbine engine compressor, at least one spiral groove formed in the surface extending axially relative to the axis, a stator blade fixed to the casing, wherein a tip of the stator blade is proximate to the at least one spiral groove.
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公开(公告)号：US11092030B2
公开(公告)日：2021-08-17
申请号：US16388199
申请日：2019-04-18
Applicant: United Technologies Corporation
Inventor： Michael M. Joly , Andrzej Ernest Kuczek , Zaffir A. Chaudhry , Gorazd Medic , Dilip Prasad
Abstract: A gas turbine engine includes a plurality of blades circumferentially spaced from each other. A plurality of rings are spaced radially outward from the plurality of blade. At least one actuator is in mechanical communication with the plurality of rings for moving the plurality of rings in an axial direction to create an axial gap adjacent at least one of the plurality of rings.
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