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公开(公告)号：US11111801B2
公开(公告)日：2021-09-07
申请号：US14787332
申请日：2014-05-21
摘要： A vane has an airfoil extending between a radially outer platform and a radially inner platform. At least one of the platforms has nominally radially thinner portions, and a pad defining a radially thicker portion. The pad has a radial thickness that is greater than a thickness of the nominal radially thinner portions. The pad surrounds an outer periphery of the airfoil on a side of the radially outer platform. The pad has a varying radial thickness. A mid-turbine frame and a gas turbine engine are also disclosed.
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公开(公告)号：US10953461B2
公开(公告)日：2021-03-23
申请号：US16360145
申请日：2019-03-21
发明人： Steven D. Porter , Jon E. Sobanski
摘要： An investment casting method includes providing a stock investment casting core, bending the stock investment casting core to thereby form a production investment casting core that conforms to a design cooling passage shape, and casting an alloy around the production investment casting core to form a cast article.
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公开(公告)号：US20200378602A1
公开(公告)日：2020-12-03
申请号：US16807478
申请日：2020-03-03
发明人： Steven D. Porter , John W. Mubeezi
摘要： A method of manufacturing a heat shield panel including pouring melted wax into a negative pattern of the heat shield panel, the heat shield panel including first pin fins with rounded tops and second pin fins with flat tops; allowing the wax to solidify to form a positive pattern of the heat shield panel; removing the positive pattern from the negative pattern by using an ejector rod to push the positive pattern away from the negative pattern at the flat top of each of the one or more second pin fins; coating the positive pattern with a ceramic; melting the positive pattern away from the ceramic, the ceramic having a cavity forming a second negative pattern of the heat shield panel; pouring melted metal into the cavity; allowing metal in the cavity to cool to form the heat shield panel; and removing the ceramic from the heat shield panel.
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公开(公告)号：US20200277867A1
公开(公告)日：2020-09-03
申请号：US16751298
申请日：2020-01-24
发明人： Steven D. Porter , Shawn M. McMahon , Kevin Zacchera , Noah Wadsworth , Christopher Whitfield , Sean D. Bradshaw , Dennis M. Moura
摘要： A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A seal assembly is disposed between the combustor and the first vane stage. The seal assembly includes a first plurality of openings and the first vane stage includes a second plurality of openings communicating cooling airflow into a gap between an aft end of the combustor and the first vane stage. A first vane stage assembly and a method are also disclosed.
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公开(公告)号：US20200041132A1
公开(公告)日：2020-02-06
申请号：US16053296
申请日：2018-08-02
发明人： Jon E. Sobanski , Steven D. Porter
摘要： A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, and a rail disposed about a periphery of the cold side, the rail including a first rail member having a first length extending along the panel, a first height extending from the cold side, and a first thickness that varies along the first length.
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公开(公告)号：US20190285276A1
公开(公告)日：2019-09-19
申请号：US15921376
申请日：2018-03-14
IPC分类号： F23R3/00
摘要： A combustor panel may comprise a surface extending from a first end of the combustor panel to a second end of the combustor panel opposite the first end. A first rail located proximate the first end may extend from the surface of the combustor panel. The first rail may define a plurality of channels. The first rail may be formed a preselected distance away from the first end of the combustor panel.
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公开(公告)号：US10323519B2
公开(公告)日：2019-06-18
申请号：US15190494
申请日：2016-06-23
摘要： A rotor disc assembly includes a rotor disc and a minidisc. The rotor disc has a first extension member, a first finger, and a second finger. The first extension member axially extends from a disc body disposed about an axis. The first finger extends axially from the first extension member. The second finger is circumferentially spaced apart from the first finger. The second finger extends axially from the first extension member. Each of the first finger and the second finger has a first portion and a second portion that extends radially from a distal end of the first portion. The minidisc is operatively connected to the rotor disc. The minidisc has an interlocking finger that radially extends from a minidisc body and is disposed between the first finger and the second finger. The interlocking finger, the first portion, and second portion define a ring groove.
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公开(公告)号：US10215098B2
公开(公告)日：2019-02-26
申请号：US14603088
申请日：2015-01-22
发明人： Anthony P. Cherolis , Jorge I. Farah , Seth A. Max , John H. Mosley , Steven D. Porter , Gregory E. Reinhardt , Kevin Zacchera
摘要： A sealing arrangement includes a turbine static structure with a seal ring having groove with a contact surface. Also included is a bearing compartment with a second contact surface, and a piston seal positioned between the turbine static structure and the bearing compartment. The piston seal includes sides configured to contact the contact surfaces and is positioned in the groove.
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公开(公告)号：US20180292089A1
公开(公告)日：2018-10-11
申请号：US15479981
申请日：2017-04-05
摘要： A combustor panel of a combustor may include a combustion facing surface and a cooling surface opposite the combustion facing surface. An attachment feature may extend from the cooling surface. The attachment feature may define a first channel extending through the attachment feature to the combustion facing surface. The combustor channel may be formed by additive manufacturing.
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公开(公告)号：US20170081967A1
公开(公告)日：2017-03-23
申请号：US15286081
申请日：2016-10-05
CPC分类号： F01D9/041 , B22C7/02 , B22C9/04 , B22C9/10 , B22C9/108 , B22C9/24 , B22D25/02 , B22D29/001 , F01D5/187 , F05D2230/21 , F05D2230/211 , Y02T50/671 , Y02T50/673 , Y02T50/676
摘要： A casting mold assembly includes an airfoil defining section and a casting core. The airfoil defining section includes an outer mold wall and a direct-shelled inner mold wall. The direct-shelled inner mold wall is disposed within a forward chordwise portion of the airfoil defining section. The direct-shelled inner mold wall includes an aft end having an external radius measuring more than about 0.075 in. (1.9 mm). The casting core is secured within an aft chordwise portion of the airfoil defining section, and includes an aft end with an external radius measuring less than about 0.075 in. (1.9 mm). A cast component and a method for making the casting mold assembly are also disclosed.
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