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公开(公告)号：US10724535B2
公开(公告)日：2020-07-28
申请号：US15812331
申请日：2017-11-14
发明人： Jason Husband , James Glaspey
摘要： A fan of a gas turbine engine is provided. The fan having: a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end and a tip portion that is secured to a shroud that circumscribes the plurality of fan blades.
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公开(公告)号：US11092020B2
公开(公告)日：2021-08-17
申请号：US16163641
申请日：2018-10-18
发明人： Jason Husband , James Glaspey , Aaron John Pepin
摘要： A rotor assembly for a gas turbine engine includes, among other things, a rotatable hub that has a metallic main body that extends along a longitudinal axis, and that has an array of annular flanges that extend about an outer periphery of the main body to define an array of annular channels along the longitudinal axis. Each of the annular channels receives a composite reinforcement member that extends about the outer periphery of the hub.
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公开(公告)号：US20150337661A1
公开(公告)日：2015-11-26
申请号：US14761360
申请日：2013-12-16
CPC分类号： F01D5/02 , F01D5/025 , F01D5/30 , F01D5/3053 , F01D11/008 , F05D2220/10 , F05D2220/36 , F05D2230/60 , F05D2240/80 , F05D2260/30 , Y02T50/671 , Y10T29/49334
摘要： Anti-rotation tabs for the platforms in the fan section of a gas turbine engine are provided. The anti-rotation tabs interface with the trailing edge of the spinner, thereby preventing the platform from rotating and twisting.
摘要翻译： 提供了用于燃气涡轮发动机的风扇部分中的平台的防旋转突出部。 防旋转翼片与旋转器的后缘接合，从而防止平台旋转和扭转。
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公开(公告)号：US20150204201A1
公开(公告)日：2015-07-23
申请号：US14421645
申请日：2013-03-15
发明人： Matthew A. Turner , Andrew G. Alarcon , James Glaspey , Brian Green , Barry M. Ford , Renee J. Jurek
CPC分类号： F01D5/30 , F01D5/02 , F01D5/143 , F01D5/145 , F01D11/008 , F05D2220/32 , F05D2240/55 , Y02T50/673
摘要： A spacer assembly for a rotor assembly of a gas turbine engine includes an endwall segment having a non-axisymmetric flowpath surface, a first depression and a second depression. A perimeter of the flowpath surface includes a forward edge, an aft edge, a suction side edge and a pressure side edge. The first depression is formed along the flowpath surface adjoining the suction side edge, and the second depression is formed along the flowpath surface adjoining the pressure side edge.
摘要翻译： 用于燃气涡轮发动机的转子组件的间隔件组件包括具有非轴对称流路表面的端壁段，第一凹陷和第二凹陷。 流路表面的周边包括前边缘，后边缘，吸力侧边缘和压力侧边缘。 第一凹部沿着与吸力侧边缘相邻的流路面形成，第二凹部沿着与压力侧边缘相邻的流路面形成。
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公开(公告)号：US11359500B2
公开(公告)日：2022-06-14
申请号：US16163654
申请日：2018-10-18
发明人： Jason Husband , James Glaspey
摘要： A platform for a gas turbine engine according to an example of the present disclosure includes, among other things, a platform body that extends in a circumferential direction between first and second sidewalls to define a gas path surface, and opposed rows of flexible retention tabs that extend from the platform body and are dimensioned to wedge the platform between adjacent airfoils.
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公开(公告)号：US11009036B2
公开(公告)日：2021-05-18
申请号：US16117500
申请日：2018-08-30
发明人： Jason Husband , James Glaspey
IPC分类号： F04D29/38 , F01D5/14 , F01D5/18 , F04D19/00 , F04D29/32 , F04D29/64 , F04D29/02 , F01D5/12 , B23P15/04
摘要： A blade for use in a gas turbine engine is disclosed. In various embodiments, the blade includes a pressure side sheath and a suction side sheath secured to the pressure side sheath. The pressure side sheath and the suction side sheath are configured to form a continuous sheath that wraps around an interior section of the blade.
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公开(公告)号：US20200072235A1
公开(公告)日：2020-03-05
申请号：US16117500
申请日：2018-08-30
发明人： Jason Husband , James Glaspey
摘要： A blade for use in a gas turbine engine is disclosed. In various embodiments, the blade includes a pressure side sheath and a suction side sheath secured to the pressure side sheath. The pressure side sheath and the suction side sheath are configured to form a continuous sheath that wraps around an interior section of the blade.
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公开(公告)号：US10533575B2
公开(公告)日：2020-01-14
申请号：US15696978
申请日：2017-09-06
发明人： Jason Husband , James Glaspey
摘要： Disclosed is a fan blade for a gas turbine engine, the fan blade having: an airfoil having a leading edge, a trailing edge, a tip, and a frangible strip connected to the blade tip and extending outwardly therefrom, the frangible strip being less resistant to plastic deformation than the fan blade tip.
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公开(公告)号：US11306601B2
公开(公告)日：2022-04-19
申请号：US16163610
申请日：2018-10-18
发明人： Jason Husband , James Glaspey
摘要： An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction, and the airfoil section defines a pressure side and a suction side separated in a thickness direction. The airfoil section includes a metallic sheath that receives a composite core, and the core includes first and second ligaments received in respective internal channels defined by the sheath such that the first and second ligaments are spaced apart along the root section with respect to the chordwise direction. The first and second ligaments define respective sets of bores, and the respective sets of bores are aligned to receive a common set of retention pins.
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公开(公告)号：US10584714B2
公开(公告)日：2020-03-10
申请号：US15812331
申请日：2017-11-14
发明人： Jason Husband , James Glaspey
摘要： A fan of a gas turbine engine is provided. The fan having: a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end and a tip portion that is secured to a shroud that circumscribes the plurality of fan blades.
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