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公开(公告)号：US11170140B2
公开(公告)日：2021-11-09
申请号：US16026627
申请日：2018-07-03
IPC分类号： G06F30/20 , G06F111/10 , G06N20/00
摘要： A method for qualifying a gas turbine engine component includes creating a first set of substantially identical gas turbine engine components via a uniform manufacturing procedure, determining a set of as-manufactured parameters of each gas turbine engine component in the first set, and determining a variance model of the first set. The variance model includes a representative parameter profile, which includes a plurality of component parameter profiles. The sum of each of the component parameter profiles is the representative parameter profile. The method also includes determining at least one predicted response models based at least in part on the variance model, identifying as-manufactured parameters of a second engine component, applying the as-manufactured parameters of the second engine component to the at least one predicted response models, thereby generating a predicted response output, and qualifying the second engine component for usage in at least one gas turbine engine corresponding to the at least one predicted response model.
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公开(公告)号：US10731473B2
公开(公告)日：2020-08-04
申请号：US16000239
申请日：2018-06-05
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a hollow vascular engineered lattice structure formed inside of the wall. The hollow vascular engineered lattice structure has an inlet hole and an outlet hole that communicate fluid into and out of the hollow vascular structure. The hollow vascular engineered lattice structure further has at least one resupply inlet hole between the inlet hole and the outlet hole with respect to a dimension of the component to communicate additional fluid into the hollow vascular engineered lattice structure.
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公开(公告)号：US20190010810A1
公开(公告)日：2019-01-10
申请号：US16126482
申请日：2018-09-10
发明人： Daniel A. Snyder , Jaimie Schweitzer , Jonathan Perry Sandoval , Edwin Otero , Kyle C. Lana , Scott D. Virkler
摘要： An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour. When the turbine blade is received in one of the plurality of slots, the lower surface of the platform is located above a portion of the upper surface of the first section of the tab, and the contour of the upper surface of the first section of the tab matches the contour of the lower surface of the platform.
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公开(公告)号：US20180347373A1
公开(公告)日：2018-12-06
申请号：US16000239
申请日：2018-06-05
CPC分类号： F01D5/186 , F01D9/02 , F01D9/041 , F01D11/08 , F01D25/12 , F04D29/526 , F04D29/5846 , F05D2220/32 , F05D2230/21 , F05D2230/30 , F05D2250/28 , F05D2260/202 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , Y02T50/673 , Y02T50/676
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things, a wall and a hollow vascular engineered lattice structure formed inside of the wall. The hollow vascular engineered lattice structure has an inlet hole and an outlet hole that communicate fluid into and out of the hollow vascular structure. The hollow vascular engineered lattice structure further has at least one resupply inlet hole between the inlet hole and the outlet hole with respect to a dimension of the component to communicate additional fluid into the hollow vascular engineered lattice structure.
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公开(公告)号：US09920627B2
公开(公告)日：2018-03-20
申请号：US14712988
申请日：2015-05-15
CPC分类号： F01D5/082 , F01D5/081 , F01D11/008 , F01D17/105 , F04D19/002 , F04D25/045 , F04D27/009 , F04D29/325 , F05D2220/32 , F05D2260/2212 , F05D2260/231 , Y02T50/676
摘要： An assembly for a gas turbine that engine includes a fan section. A turbine section is configured to drive the fan section. The turbine section includes a rotor hub with a rotor lug. A heat shield engages the rotor lug. The heat shield and the rotor lug define a cooling passage.
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公开(公告)号：US09810087B2
公开(公告)日：2017-11-07
申请号：US14748876
申请日：2015-06-24
CPC分类号： F01D11/006 , F01D5/081 , F01D5/22 , F01D5/3015 , F01D11/008 , F02C7/18 , F05D2220/32 , F05D2240/24 , F05D2240/55 , F05D2250/72 , F05D2260/20 , F16J15/02 , Y02T50/676
摘要： A sealing structure for a gas turbine engine includes a rotor that has a rim with slots and a cooling passage. The rotor is rotatable about an axis. First and second blades are arranged in the slots and respectively including first and second shelves facing one another within a pocket that is in fluid communication with the cooling passage. The first and second shelves form an opening. A reversible seal is arranged within the pocket and has a body that is configured for operative association with the first and second blades in any of four orientations to seal the opening in a second condition. The seal includes first and second protrusions respectively extending from first and second faces opposing one another. The first protrusions supported on the rim in a first condition.
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公开(公告)号：US09726023B2
公开(公告)日：2017-08-08
申请号：US14605366
申请日：2015-01-26
CPC分类号： F01D5/187 , F01D5/147 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2240/35 , F05D2260/22141 , Y02T50/676
摘要： In various embodiments, an airfoil used as a turbine blade for a turbine wheel in a gas turbine engine is provided. The airfoil may comprise a root, a tip, and a body. The root may have a first area. The tip may have a second area. The body may have a chord bounded by the root and the tip. The body may also define a cooling chamber. The cooling chamber may have a first rib substantially perpendicular to the chord. The cooling chamber may also have a second rib extending partially between the root and the tip.
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公开(公告)号：US10907482B2
公开(公告)日：2021-02-02
申请号：US16126482
申请日：2018-09-10
发明人： Daniel A. Snyder , Jaimie Schweitzer , Jonathan Perry Sandoval , Edwin Otero , Kyle C. Lana , Scott D. Virkler
摘要： An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour. When the turbine blade is received in one of the plurality of slots, the lower surface of the platform is located above a portion of the upper surface of the first section of the tab, and the contour of the upper surface of the first section of the tab matches the contour of the lower surface of the platform.
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公开(公告)号：US20160298466A1
公开(公告)日：2016-10-13
申请号：US14680139
申请日：2015-04-07
发明人： Daniel A. Snyder
CPC分类号： F01D5/22 , F01D5/3007 , F01D11/006 , F01D25/06 , F05D2220/32 , F05D2240/80
摘要： An exemplary gas turbine engine assembly includes a damping device having a first side and a second side facing away from the first side. The first side is configured to hold a seal when the second side engages an extension from a gas turbine engine component. The first side is further configured to engage the extension when the second side holds the seal.
摘要翻译： 示例性的燃气涡轮发动机组件包括具有第一侧和远离第一侧的第二侧的阻尼装置。 第一侧构造成当第二侧接合来自燃气涡轮发动机部件的延伸部时保持密封。 第一侧进一步构造成当第二侧保持密封时接合延伸部。
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10.发明申请Additive Manufactured Inseparable Platform Damper and Seal Assembly for a Gas Turbine Engine 有权用于燃气轮机发动机的添加剂制造的不可分离的平台阻尼器和密封组件公开(公告)号：US20160222798A1
公开(公告)日：2016-08-04
申请号：US14613724
申请日：2015-02-04
CPC分类号： F01D5/22 , B22F3/1055 , B22F5/009 , B22F7/00 , B29C64/153 , B33Y80/00 , F01D11/006 , F01D11/008 , F01D25/06 , F05D2230/22 , F05D2260/96 , Y02P10/295
摘要： A damper-seal assembly for a gas turbine engine includes an additively manufactured seal and an additively manufactured damper inseparably assembled with the additively manufactured seal.
摘要翻译： 用于燃气涡轮发动机的阻尼器密封组件包括相加制造的密封件和与加法制造的密封件不可分离地组装的附加制造的阻尼器。
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