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公开(公告)号：US20180209274A1
公开(公告)日：2018-07-26
申请号：US15415164
申请日：2017-01-25
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Brandon Wayne Miller , Richard Wesling , Gert Johannes van der Merwe
IPC: F01D5/08 , F02K3/06 , F01D5/22 , F04D29/32 , F04D29/053
Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a first turbine rotor comprising an inner shroud, an outer shroud outward of the inner shroud in the radial direction, at least one connecting airfoil coupling the inner shroud and the outer shroud at least partially along the radial direction, and an outer band outward of the outer shroud in the radial direction and extended at least partially in the circumferential direction, and a plurality of connecting members couples the outer shroud and the outer band.
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公开(公告)号：US10294821B2
公开(公告)日：2019-05-21
申请号：US15485515
申请日：2017-04-12
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Alan Roy Stuart , Jeffrey Donald Clements , Brandon Wayne Miller , Darek Tomasz Zatorski , Gert Johannes van der Merwe , Joel Francis Kirk , Richard Wesling
Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction, and wherein the gas turbine engine defines a core flowpath extended generally along the longitudinal direction. The gas turbine engine includes a turbine frame defined around the axial centerline, the turbine frame comprising a first bearing surface disposed inward along the radial direction. The gas turbine engine further includes a turbine rotor assembly including a bearing assembly coupled to the first bearing surface of the turbine frame and the turbine rotor assembly. The turbine rotor assembly further includes a first turbine rotor disposed upstream of the turbine frame and a second turbine rotor disposed downstream of the turbine frame. The first turbine rotor and the second turbine rotor are rotatable together about the axial centerline.
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公开(公告)号：US10544793B2
公开(公告)日：2020-01-28
申请号：US15415164
申请日：2017-01-25
Applicant: General Electric Company
Inventor： Darek Tomasz Zatorski , Brandon Wayne Miller , Richard Wesling , Gert Johannes van der Merwe
IPC: F04D29/00 , F04D29/053 , F01D5/18 , F01D11/16 , F01D25/12
Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction. The gas turbine engine includes a first turbine rotor comprising an inner shroud, an outer shroud outward of the inner shroud in the radial direction, at least one connecting airfoil coupling the inner shroud and the outer shroud at least partially along the radial direction, and an outer band outward of the outer shroud in the radial direction and extended at least partially in the circumferential direction, and a plurality of connecting members couples the outer shroud and the outer band.
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公开(公告)号：US20180298784A1
公开(公告)日：2018-10-18
申请号：US15485515
申请日：2017-04-12
Applicant: General Electric Company
Inventor： Thomas Ory Moniz , Alan Roy Stuart , Jeffrey Donald Clements , Brandon Wayne Miller , Darek Tomasz Zatorski , Gert Johannes van der Merwe , Joel Francis Kirk , Richard Wesling
CPC classification number: F01D25/183 , F01D25/162
Abstract: The present disclosure is directed to a gas turbine engine defining a radial direction, a circumferential direction, an axial centerline along a longitudinal direction, and wherein the gas turbine engine defines an upstream end and a downstream end along the longitudinal direction, and wherein the gas turbine engine defines a core flowpath extended generally along the longitudinal direction. The gas turbine engine includes a turbine frame defined around the axial centerline, the turbine frame comprising a first bearing surface disposed inward along the radial direction. The gas turbine engine further includes a turbine rotor assembly including a bearing assembly coupled to the first bearing surface of the turbine frame and the turbine rotor assembly. The turbine rotor assembly further includes a first turbine rotor disposed upstream of the turbine frame and a second turbine rotor disposed downstream of the turbine frame. The first turbine rotor and the second turbine rotor are rotatable together about the axial centerline.
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