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公开(公告)号：US20170175551A1
公开(公告)日：2017-06-22
申请号：US14974150
申请日：2015-12-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ryan Alan Waite
CPC classification number: F01D5/189 , F01D5/188 , F01D9/02 , F01D11/10 , F01D25/12 , F02C7/12 , F05D2220/32 , F05D2240/11 , F05D2260/20 , F05D2260/201 , F05D2260/202 , Y02T50/676
Abstract: According to one aspect of the present disclosure, an engine component for a gas turbine engine is disclosed that includes an internal cavity and a baffle. The internal cavity is defined by the engine component, and the internal cavity is in fluid communication with a source of cooling air. The baffle is disposed within the internal cavity, and includes at least four longitudinal sidewalls that include at least two first sidewalls, one of which is upstream and one of which is downstream, and at least two second sidewalls, at least one of which faces towards a core flow path of the gas turbine engine. The baffle includes a plurality of openings for directing cooling air from within the baffle into the cavity. A majority of the openings are on at least one of the first sidewalls.
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公开(公告)号：US20160230596A1
公开(公告)日：2016-08-11
申请号：US15022943
申请日：2014-10-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin F. Hagan , Ryan Alan Waite
CPC classification number: F01D25/12 , F01D5/187 , F01D9/041 , F01D9/065 , F04D29/542 , F04D29/5846 , F05D2220/32 , F05D2240/81 , F05D2260/202 , F05D2260/204 , Y02T50/676
Abstract: A gas turbine engine component has an airfoil extending radially inwardly of an outer platform to an inner platform. A central passage is formed within the airfoil and has an inlet end for receiving cooling air. An outlet end in the inner platform delivers cooling air to a downstream use. The airfoil has a suction wall and a pressure wall, and extends in an axial direction from a leading edge to a trailing edge. A suction skin core is between the central passage and the suction wall. A pressure skin core is between the central passage and the pressure wall.
Abstract translation: 燃气涡轮发动机部件具有从外平台径向向内延伸到内平台的翼型件。 中心通道形成在翼型内，并具有用于接收冷却空气的入口端。 内平台中的出口端将冷却空气输送到下游使用。 翼型件具有抽吸壁和压力壁，并且在从前缘到后缘的轴向方向上延伸。 吸力皮芯位于中央通道和吸壁之间。 压力皮芯位于中央通道和压壁之间。
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公开(公告)号：US20160208618A1
公开(公告)日：2016-07-21
申请号：US14600048
申请日：2015-01-20
Applicant: United Technologies Corporation
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Bryan P. Dube , Dominic J. Mongillo, JR.
CPC classification number: F01D5/187 , F01D5/147 , F01D5/18 , F01D5/225 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/211 , F05D2240/12 , F05D2240/30 , F05D2240/81 , F05D2260/202 , F05D2260/22141
Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots.
Abstract translation: 机翼包括具有平台前端和后端，侧面以及内外表面的平台。 翼面部分从平台的内表面向外延伸。 机翼部分包括翼型件的前端和后端以及连接翼型件前端和后端的侧壁。 该平台包括一个冷却通道，该冷却通道在前部位置具有一个入口，在该平台后端具有一个出口槽，以及一个从入口延伸到出口槽的中间通道部分。 中间通道部分包括供给出口槽的公共歧管区域。
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公开(公告)号：US10808549B2
公开(公告)日：2020-10-20
申请号：US16049987
申请日：2018-07-31
Applicant: United Technologies Corporation
Inventor： Benjamin F. Hagan , Ryan Alan Waite , Bryan P. Dube , Dominic J. Mongillo, Jr.
Abstract: An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots. The platform includes a rib that is elongated in a length direction between the platform leading and trailing ends. The rib divides two of the cooling passages such that the two cooling passages are fluidly unconnected with each other in the platform.
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公开(公告)号：US10465542B2
公开(公告)日：2019-11-05
申请号：US15708603
申请日：2017-09-19
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Ryan Alan Waite , Steven Bruce Gautschi , Benjamin F. Hagan
Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend between at least one of the pressure and suction side walls into the airfoil cavity to support the baffle relative to the at least one of the pressure and suction side walls. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through the at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.
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Patent Agency Ranking
公开(公告)号：US10378381B2
公开(公告)日：2019-08-13
申请号：US15022943
申请日：2014-10-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Benjamin F. Hagan , Ryan Alan Waite
Abstract: A gas turbine engine component has an airfoil extending radially inwardly of an outer platform to an inner platform. A central passage is formed within the airfoil and has an inlet end for receiving cooling air. An outlet end in the inner platform delivers cooling air to a downstream use. The airfoil has a suction wall and a pressure wall, and extends in an axial direction from a leading edge to a trailing edge. A suction skin core is between the central passage and the suction wall. A pressure skin core is between the central passage and the pressure wall.
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公开(公告)号：US10156147B2
公开(公告)日：2018-12-18
申请号：US14974150
申请日：2015-12-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Ryan Alan Waite
Abstract: According to one aspect of the present disclosure, an engine component for a gas turbine engine is disclosed that includes an internal cavity and a baffle. The internal cavity is defined by the engine component, and the internal cavity is in fluid communication with a source of cooling air. The baffle is disposed within the internal cavity, and includes at least four longitudinal sidewalls that include at least two first sidewalls, one of which is upstream and one of which is downstream, and at least two second sidewalls, at least one of which faces towards a core flow path of the gas turbine engine. The baffle includes a plurality of openings for directing cooling air from within the baffle into the cavity. A majority of the openings are on at least one of the first sidewalls.
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公开(公告)号：US20180023407A1
公开(公告)日：2018-01-25
申请号：US15708603
申请日：2017-09-19
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Ryan Alan Waite , Steven Bruce Gautschi , Benjamin F. Hagan
CPC classification number: F01D9/065 , F01D5/186 , F01D5/187 , F01D25/12 , F01D25/14 , F05D2240/126 , F05D2260/20 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/673 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend between at least one of the pressure and suction side walls into the airfoil cavity to support the baffle relative to the at least one of the pressure and suction side walls. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through the at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.
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公开(公告)号：US20170298762A1
公开(公告)日：2017-10-19
申请号：US14615509
申请日：2015-02-06
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Ryan Alan Waite , Steven Bruce Gautschi , Benjamin F. Hagan
CPC classification number: F01D9/065 , F01D5/186 , F01D5/187 , F01D25/12 , F01D25/14 , F05D2240/126 , F05D2260/20 , F05D2260/202 , F05D2260/204 , Y02T50/672 , Y02T50/676
Abstract: An airfoil for a gas turbine engine includes pressure and suction side walls joined to one another at leading and trailing edges. The pressure and suction side walls surround an airfoil cavity and provide an exterior airfoil surface. A baffle is arranged in the airfoil cavity and includes a supply hole. Ribs extend from the pressure and suction side walls into the airfoil cavity and engage the baffle. The ribs are configured to provide a serpentine cooling passage between the baffle and at least one of the pressure and suction side walls. The serpentine cooling passage has first and second passes joined by a bend. The ribs form a film cooling cavity between the first and second passes. The supply hole fluidly connects the baffle to the film cooling cavity. Film cooling holes extend through at least one of the pressure and suction side walls. The film cooling holes are in fluid communication with the film cooling cavity.
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公开(公告)号：US09771814B2
公开(公告)日：2017-09-26
申请号：US14641470
申请日：2015-03-09
Applicant: United Technologies Corporation
Inventor： Brandon W. Spangler , Ky H. Vu , Jeffrey J. DeGray , Ryan Alan Waite , Gina Cavallo , Thomas P. Dziuba
CPC classification number: F01D9/041 , F01D5/02 , F01D5/186 , F01D5/189 , F01D9/065 , F01D25/12 , F04D29/321 , F05D2220/32 , F05D2230/21 , F05D2230/642 , F05D2240/126 , F05D2240/80 , F05D2260/20 , F05D2260/30 , Y02T50/676
Abstract: A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.
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