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公开(公告)号：US11242769B2
公开(公告)日：2022-02-08
申请号：US16221991
申请日：2018-12-17
Applicant: United Technologies Corporation
Inventor： Vijay Narayan Jagdale , Jesse R. Boyer , Om P. Sharma , Evan Butcher , Lawrence Binek , Bryan G. Dods
Abstract: A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.
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公开(公告)号：US20200248560A1
公开(公告)日：2020-08-06
申请号：US16781829
申请日：2020-02-04
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Michael M. Joly , Dilip Prasad , Om P. Sharma
Abstract: A tandem fan for a boundary layer ingestion engine is disclosed. In various embodiments, the tandem fan includes a fan disk configured for rotation about a longitudinal axis; a primary fan blade extending radially from the fan disk, the primary fan blade having a primary fan blade span; and a secondary fan blade extending radially from the fan disk, the secondary fan blade having a secondary fan blade span within about ninety percent to about one-hundred percent of the primary fan blade span.
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公开(公告)号：US20150227677A1
公开(公告)日：2015-08-13
申请号：US14428021
申请日：2013-02-17
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Om P. Sharma , Michael F. Blair
CPC classification number: G06F17/5086 , F01D9/02 , F01D9/023 , F02C3/10
Abstract: A gas turbine engine design process includes the steps of determining the location of a hot streak downstream of a combustor nozzle, and determining whether it would be most beneficial to have the hot streak initially impact a pressure side of a first static turbine vane or whether it would be more beneficial to have it impact a suction side. A location is designed for the first static turbine vane such that the hot streak will impact the more beneficial side of the first static turbine vane.
Abstract translation: 燃气涡轮发动机设计过程包括以下步骤：确定燃烧器喷嘴下游的热条的位置，以及确定是否最有利的是使热条件最初影响第一静态涡轮叶片的压力侧，或者是否 将会更有利于使其影响吸力。 一个位置被设计用于第一静态涡轮叶片，使得热条纹将影响第一静态涡轮叶片的更有利的侧面。
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公开(公告)号：US10907544B2
公开(公告)日：2021-02-02
申请号：US14665081
申请日：2015-03-23
Applicant: United Technologies Corporation
Inventor： Dmytro Mykolayovych Voytovych , Om P. Sharma
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.
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公开(公告)号：US10330010B2
公开(公告)日：2019-06-25
申请号：US14967518
申请日：2015-12-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler , William K. Ackermann , Matthew R. Feulner , Om P. Sharma
Abstract: A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.
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Patent Agency Ranking
公开(公告)号：US20170167384A1
公开(公告)日：2017-06-15
申请号：US14967518
申请日：2015-12-14
Applicant: United Technologies Corporation
Inventor： Gabriel L. Suciu , Brian D. Merry , Jesse M. Chandler , William K. Ackermann , Matthew R. Feulner , Om P. Sharma
CPC classification number: F02C7/18 , F01D5/08 , F02C3/04 , F02C7/143 , F02C7/185 , F02C9/18 , F02K3/06 , F04D27/0215 , F04D29/582 , F05D2220/32 , F05D2220/3219 , F05D2240/24 , F05D2260/205 , F05D2260/211 , F05D2260/213 , Y02T50/676
Abstract: A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.
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公开(公告)号：US11162416B2
公开(公告)日：2021-11-02
申请号：US16222109
申请日：2018-12-17
Applicant: United Technologies Corporation
Inventor： Evan Butcher , Jesse R. Boyer , Om P. Sharma , Lawrence Binek , Bryan G. Dods , Vijay Narayan Jagdale
IPC: F02C6/20 , F01D25/24 , B60K3/04 , B33Y10/00 , B33Y80/00 , F01D25/26 , F01D25/28 , F02C7/20 , F02K1/80
Abstract: A vehicle structure with unitary casing for an attritable gas turbine engine comprising a vehicle structure forming a unitary casing having a casing wall opposite the vehicle structure; a bypass duct formed between the casing wall and the vehicle structure, wherein the unitary casing is configured to receive a core of the attritable gas turbine engine.
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公开(公告)号：US10808545B2
公开(公告)日：2020-10-20
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
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：US20200318549A1
公开(公告)日：2020-10-08
申请号：US16375018
申请日：2019-04-04
Applicant: United Technologies Corporation
Inventor： Georgi Kalitzin , Gorazd Medic , Om P. Sharma , Timothy S. Snyder , Graham B. Fulton, III
Abstract: A combustor for use in a gas turbine engine including: a radially inward heat shield panel; and a radially outward heat shield panel located radially outward of the radially inward heat shield panel, the radially inward heat shield panel and the radially outward heat shield panel being in a facing spaced relationship defining a combustion chamber therebetween, wherein at least one of the radially inward heat shield panel and the radially outward heat shield panel has a non-axisymmetric shape.
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公开(公告)号：US20190153866A1
公开(公告)日：2019-05-23
申请号：US15819047
申请日：2017-11-21
Applicant: United Technologies Corporation
Inventor： Dmytro Mykolayovych Voytovych , Alexander Staroselsky , Om P. Sharma , Gabriel L. Suciu , Brian Merry , Ioannis Alvanos
Abstract: An exemplary gas turbine engine includes a turbine section and a fan mechanically connected to the turbine section such that rotation of the turbine drives rotation of the fan. The fan includes a hub, a plurality of blade bodies extending radially outward from the hub to a first partial shroud, and a plurality of blade tips extending radially outward from the partial shroud.
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