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公开(公告)号：US10364679B2
公开(公告)日：2019-07-30
申请号：US15102341
申请日：2014-12-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark F. Zelesky , Michael Winter , Paul E. Coderre , Richard L. Sykes
Abstract: A gas turbine engine rotor includes a rotor that provides a cooling cavity. The cooling cavity has a first chamber and a second chamber that are fluidly connected to one another by a passageway. At least one of the first and second rotor portions is configured to support a blade that is fluidly isolated from the cavity. A phase change material is arranged in the cavity. The phase change material is configured to be arranged in the first chamber in a first state and in the second chamber in the second state. The passageway is configured to carry the phase change material between the second and first chambers once changed between the first and second states.
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2.发明授权公开(公告)号：US11293298B2
公开(公告)日：2022-04-05
申请号：US16704642
申请日：2019-12-05
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto , Paul E. Coderre , Horacio Antonio Altagracia
Abstract: A compressor case to blade tip clearance system comprising a rotor having blades with tips, the case including an inner case comprising at least one surface feature fluidly coupled to a distribution manifold disposed in a cooling air passageway, the at least one surface feature configured to interact with the cooling air, and a tip clearance located between the tips and the inner case; wherein the tip clearance is maintained responsive to a flow of the cooling air over the at least one surface feature.
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3.发明申请公开(公告)号：US20210172332A1
公开(公告)日：2021-06-10
申请号：US16704642
申请日：2019-12-05
Applicant: United Technologies Corporation
Inventor： Enzo DiBenedetto , Paul E. Coderre
Abstract: A compressor case to blade tip clearance system comprising a rotor having blades with tips, the case including an inner case comprising at least one surface feature fluidly coupled to a distribution manifold disposed in a cooling air passageway, the at least one surface feature configured to interact with the cooling air, and a tip clearance located between the tips and the inner case; wherein the tip clearance is maintained responsive to a flow of the cooling air over the at least one surface feature.
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公开(公告)号：US20170002834A1
公开(公告)日：2017-01-05
申请号：US14902373
申请日：2014-07-10
Applicant: United Technologies Corporation
Inventor： Brad Powell , Anthony R. Bifulco , Paul E. Coderre
CPC classification number: F04D29/5826 , F01D5/082 , F01D5/084 , F02C7/185 , F04B1/2064 , F04B1/324 , F04D19/02 , F04D27/002 , F04D29/321 , F04D29/5833 , F04D29/584 , F05B2220/302
Abstract: An example method of cooling a compressor section of a gas turbine engine includes diverting a flow from a compressor through a heat exchanger, the flow moving from the compressor in a first direction, and moving the flow from the heat exchanger back to the compressor in a second direction. An example spacer for a compressor of a gas turbine engine includes a first side portion, a second side portion spaced apart from the first side portion, and a middle web arranged between the first and second side portions. At least one of the first and second side portions and the middle web include at least one orifice to communicate flow in a direction that is different from a core flowpath flow direction. An example compressor including the spacer is also disclosed.
Abstract translation: 一种冷却燃气涡轮发动机的压缩机部分的示例性方法包括使来自压缩机的流动通过热交换器转向，该流量从压缩机沿第一方向移动，并且将流体从热交换器移回到压缩机中 第二个方向 用于燃气涡轮发动机的压缩机的示例性间隔件包括第一侧部分，与第一侧部分间隔开的第二侧部以及布置在第一和第二侧部之间的中间腹板。 第一和第二侧部和中间腹板中的至少一个包括至少一个孔，以在不同于芯流路流动方向的方向上传递流。 还公开了包括间隔件的示例性压缩机。
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公开(公告)号：US09188009B2
公开(公告)日：2015-11-17
申请号：US13663665
申请日：2012-10-30
Applicant: United Technologies Corporation
Inventor： Cagdas Yilmaz , Paul E. Coderre
CPC classification number: F01D5/085 , F01D5/081 , F02C7/12 , F05D2260/213 , Y02T50/676
Abstract: A gas turbine engine includes a rotor having at least one rotor bore cavity and a heat exchanger. The heat exchanger is fluidically connected to a conditioning air source and to the rotor bore cavity for flowing air from the conditioning air source to the rotor bore cavity. The heat exchanger is also fluidically connected to a hot fluid source and a cool fluid source for selectively heating and cooling conditioning air flowing to the rotor bore cavity.
Abstract translation: 燃气涡轮发动机包括具有至少一个转子孔腔和热交换器的转子。 热交换器流体连接到调节空气源和转子孔腔，用于将空气从调节空气源流到转子孔腔。 热交换器还流体连接到热流体源和冷流体源，用于选择性地加热和冷却调节流到转子孔腔的空气。
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Patent Agency Ranking
公开(公告)号：US10480533B2
公开(公告)日：2019-11-19
申请号：US14916425
申请日：2014-09-08
Applicant: United Technologies Corporation
Inventor： Brad Powell , Anthony R. Bifulco , Paul E. Coderre , John P. Virtue , Brian Lucker
Abstract: An example method of cooling a compressor of a gas turbine includes, among other things, diverting a flow from a compressor, and directing the flow at the compressor in a direction, the direction having a circumferential component and an axial component.
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公开(公告)号：US20190211683A1
公开(公告)日：2019-07-11
申请号：US15864925
申请日：2018-01-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Matthew E. Bintz , Enzo DiBenedetto , Paul E. Coderre
CPC classification number: F01D5/087 , F01D5/06 , F01D11/001 , F01D11/02 , F02C7/141 , F02C7/18 , F04D29/321 , F04D29/582 , F05D2210/12 , F05D2220/3218 , F05D2220/3219 , F05D2240/11 , F05D2240/12 , F05D2240/24 , F05D2240/55 , F05D2260/20 , F05D2260/209 , F05D2260/213
Abstract: A gas turbine engine is disclosed. The gas turbine engine includes a first rotor supporting a first plurality of circumferentially spaced rotor blades and a second rotor disposed axially downstream of the first rotor and supporting a second plurality of circumferentially spaced rotor blades, a first bore cavity between the first rotor and the second rotor, a first fluid passageway configured to provide cooled air to the first bore cavity and a first anti-vortex component positioned proximate the first bore cavity and configured to increase pressure of the cooled air as the cooled air traverses radially outward from the first bore cavity.
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公开(公告)号：US20160319667A1
公开(公告)日：2016-11-03
申请号：US15102341
申请日：2014-12-02
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Mark F. Zelesky , Michael Winter , Paul E. Coderre , Richard L. Sykes
CPC classification number: F01D5/088 , F01D5/181 , F01D5/34 , F02C3/04 , F02C7/16 , F05D2220/32 , F05D2240/81 , F05D2260/207 , F05D2260/208 , F05D2260/232 , Y02T50/676
Abstract: A gas turbine engine rotor includes a rotor that provides a cooling cavity. The cooling cavity has a first chamber and a second chamber that are fluidly connected to one another by a passageway. At least one of the first and second rotor portions is configured to support a blade that is fluidly isolated from the cavity. A phase change material is arranged in the cavity. The phase change material is configured to be arranged in the first chamber in a first state and in the second chamber in the second state. The passageway is configured to carry the phase change material between the second and first chambers once changed between the first and second states.
Abstract translation: 燃气涡轮发动机转子包括提供冷却腔的转子。 冷却腔具有通过通道彼此流体连接的第一腔室和第二腔室。 第一和第二转子部分中的至少一个构造成支撑与空腔流体隔离的叶片。 相变材料布置在空腔中。 相变材料构造成在第一状态下布置在第一室中，并且在第二状态下布置在第二室中。 通道构造成在第一和第二状态之间改变之后，在第二腔室和第一腔室之间承载相变材料。
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公开(公告)号：US20160222982A1
公开(公告)日：2016-08-04
申请号：US14916425
申请日：2014-09-08
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Brad Powell , Anthony R. Bifulco , Paul E. Coderre , John P. Virtue , Brian Lucker
CPC classification number: F04D29/5846 , F01D9/065 , F01D25/125 , F02C7/14 , F02K3/04 , F04D29/321 , F04D29/541 , F04D29/5826 , F04D29/584 , F05D2220/3219 , F05D2220/36 , F05D2240/127 , F05D2260/20 , F05D2260/213
Abstract: An example method of cooling a compressor of a gas turbine includes, among other things, diverting a flow from a compressor, and directing the flow at the compressor in a direction, the direction having a circumferential component and an axial component.
Abstract translation: 对燃气轮机的压缩机进行冷却的一个示例性方法包括：将来自压缩机的流转向转向并沿着具有圆周分量和轴向分量的方向的压缩机的流动。
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公开(公告)号：US20140219794A1
公开(公告)日：2014-08-07
申请号：US13663665
申请日：2012-10-30
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Cagdas Yilmaz , Paul E. Coderre
IPC: F01D5/08
CPC classification number: F01D5/085 , F01D5/081 , F02C7/12 , F05D2260/213 , Y02T50/676
Abstract: A gas turbine engine includes a rotor having at least one rotor bore cavity and a heat exchanger. The heat exchanger is fluidically connected to a conditioning air source and to the rotor bore cavity for flowing air from the conditioning air source to the rotor bore cavity. The heat exchanger is also fluidically connected to a hot fluid source and a cool fluid source for selectively heating and cooling conditioning air flowing to the rotor bore cavity.
Abstract translation: 燃气涡轮发动机包括具有至少一个转子孔腔和热交换器的转子。 热交换器流体连接到调节空气源和转子孔腔，用于将空气从调节空气源流到转子孔腔。 热交换器还流体连接到热流体源和冷流体源，用于选择性地加热和冷却调节流到转子孔腔的空气。
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