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公开(公告)号：US20190017388A1
公开(公告)日：2019-01-17
申请号：US15650107
申请日：2017-07-14
Applicant: United Technologies Corporation
Inventor： Tahany Ibrahim El-Wardany , Matthew E. Lynch , Om P. Sharma , Catalin G. Fotache
CPC classification number: F01D5/183 , B22F3/1115 , F01D5/147 , F04D29/023 , F04D29/324 , F04D29/388 , F05B2260/203 , F05D2220/36 , F05D2230/31 , F05D2240/305 , F05D2240/306 , F05D2300/121 , F05D2300/133 , F05D2300/514 , F05D2300/612
Abstract: An embodiment of a fan blade includes an interior region between a metallic pressure sidewall and a metallic suction sidewall. Each sidewall extends in span from a base to a tip, and extends in chord from a leading edge to a trailing edge. The interior region of the fan blade includes a first fully dense metallic portion and a first porous metallic portion. The first fully dense metallic portion has a volume occupying at least 10% of a total volume of the interior region, and substantially no porosity. The first porous metallic portion is integrally joined to the fully dense metallic portion, and is selected from a structured lattice, an unstructured foam, and combinations thereof.
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公开(公告)号：US11519289B2
公开(公告)日：2022-12-06
申请号：US16706058
申请日：2019-12-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Gabriel L. Suciu , Om P. Sharma , Joseph B. Staubach , Marc J. Muldoon , Jesse M. Chandler , David Lei Ma
Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.
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公开(公告)号：US11199136B2
公开(公告)日：2021-12-14
申请号：US16152848
申请日：2018-10-05
Applicant: United Technologies Corporation
Inventor： Evan Butcher , Jesse R. Boyer , Om P. Sharma , Lawrence Binek , Bryan G. Dods , Vijay Narayan Jagdale
Abstract: An additively manufactured thermally insulating structure comprising a base layer and a fire-resistant layer adjacent to the base layer that forms an air gap therebetween. A method for assembling a miniature gas turbine engine includes additively manufacturing an additively manufactured thermally insulating structure onto a static structure of the miniature gas turbine engine.
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公开(公告)号：US11156156B2
公开(公告)日：2021-10-26
申请号：US16151728
申请日：2018-10-04
Applicant: United Technologies Corporation
Inventor： Lawrence Binek , Jesse R. Boyer , Om P. Sharma , Evan Butcher , Bryan G. Dods , Vijay Narayan Jagdale
Abstract: A gas turbine engine is provided that includes a compressor section, a turbine section, and a unitary structure. The compressor section has at least one compressor rotor stage. The turbine section has at least one turbine rotor stage. The compressor rotor stage and the turbine rotor stage are in rotational communication with each other. The unitary structure includes an outer case portion, a combustor section, a turbine nozzle, and an exhaust duct. The unitary structure configured for attachment with the turbine section and compressor section.
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Patent Agency Ranking
公开(公告)号：US11136895B2
公开(公告)日：2021-10-05
申请号：US16268683
申请日：2019-02-06
Applicant: United Technologies Corporation
Inventor： Georgi Kalitzin , Gorazd Medic , Om P. Sharma , Junsok Yi , Dilip Prasad
Abstract: A casing treatment comprising a hub having a surface, the hub being rotatable about an axis within a casing of a gas turbine engine compressor, at least one spiral groove formed in the surface extending axially relative to the axis, a stator blade fixed to the casing, wherein a tip of the stator blade is proximate to the at least one spiral groove.
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公开(公告)号：US20210172333A1
公开(公告)日：2021-06-10
申请号：US16706058
申请日：2019-12-06
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： GABRIEL L. SUCIU , Om P. Sharma , Joseph B. Staubach , Marc J. Muldoon , Jesse M. Chandler , David Lei Ma
Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, and an electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft.
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公开(公告)号：US20200248575A1
公开(公告)日：2020-08-06
申请号：US16268683
申请日：2019-02-06
Applicant: United Technologies Corporation
Inventor： Georgi Kalitzin , Gorazd Medic , Om P. Sharma , Junsok Yi , Dilip Prasad
IPC: F01D11/00
Abstract: A casing treatment comprising a hub having a surface, the hub being rotatable about an axis within a casing of a gas turbine engine compressor, at least one spiral groove formed in the surface extending axially relative to the axis, a stator blade fixed to the casing, wherein a tip of the stator blade is proximate to the at least one spiral groove.
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公开(公告)号：US20200182155A1
公开(公告)日：2020-06-11
申请号：US16213047
申请日：2018-12-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Lawrence Binek , Evan Butcher , Jesse R. Boyer , Om P. Sharma , Bryan G. Dods , Vijay Narayan Jagdale
Abstract: A propulsion system according to an example of the present disclosure, includes a core engine and an outer casing surrounding the core engine. The outer casing includes an integral injector assembly. The injector assembly includes a wall that defines a cavity, the wall being integral with the outer casing. A method of operating a propulsion system and method of making a component of a propulsion system are also disclosed.
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公开(公告)号：US20150321764A1
公开(公告)日：2015-11-12
申请号：US14665081
申请日：2015-03-23
Applicant: United Technologies Corporation
Inventor： Dmytro Mykolayovych Voytovych , Om P. Sharma
CPC classification number: F02C7/04 , B64C2039/105 , B64D27/00 , B64D27/14 , B64D33/02 , F01D5/02 , F05D2250/14 , F05D2250/312 , Y02T50/12
Abstract: A gas turbine engine includes an inlet duct that is formed with a generally elliptical shape. The inlet duct includes a vertical centerline and a fan section that has an axis of rotation. The axis of rotation is spaced from the vertical centerline and is disposed within an inlet duct orifice.
Abstract translation: 燃气涡轮发动机包括形成为大致椭圆形状的入口管道。 入口管道包括垂直中心线和具有旋转轴线的风扇部分。 旋转轴线与垂直中心线间隔开并设置在入口管道孔内。
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