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公开(公告)号：US11078805B2
公开(公告)日：2021-08-03
申请号：US16384076
申请日：2019-04-15
Applicant: United Technologies Corporation
Inventor： Michael M. Joly , Simon W. Evans , Dilip Prasad , Gorazd Medic , Georgi Kalitzin , Dmytro Mykolayovych Voytovych
Abstract: A compressor for use in a gas turbine engine including: an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine; a casing, the casing including a radially inward surface; and a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and wherein the forward groove wall is operably shaped to generate an aft directed jet.
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公开(公告)号：US11111811B2
公开(公告)日：2021-09-07
申请号：US16460060
申请日：2019-07-02
Applicant: United Technologies Corporation
Inventor： Michael M. Joly , Zaffir A. Chaudhry , Simon W. Evans , Gorazd Medic , Dilip Prasad
Abstract: A stator vane for a gas turbine engine section includes a stator vane having an airfoil extending between a leading edge and a trailing edge. The airfoil has a suction side and a pressure side. There is at least one piezoelectric actuator for changing a shape of at least one of the leading edge and the trailing edge. A gas turbine engine is also disclosed.
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Patent Agency Ranking
公开(公告)号：US20210003030A1
公开(公告)日：2021-01-07
申请号：US16460060
申请日：2019-07-02
Applicant: United Technologies Corporation
Inventor： Michael M. Joly , Zaffir A. Chaudhry , Simon W. Evans , Gorazd Medic , Dilip Prasad
Abstract: A stator vane for a gas turbine engine section includes a stator vane having an airfoil extending between a leading edge and a trailing edge. The airfoil has a suction side and a pressure side. There is at least one piezoelectric actuator for changing a shape of at least one of the leading edge and the trailing edge. A gas turbine engine is also disclosed.
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4.发明申请公开(公告)号：US20200325790A1
公开(公告)日：2020-10-15
申请号：US16384076
申请日：2019-04-15
Applicant: United Technologies Corporation
Inventor： Michael M. Joly , Simon W. Evans , Dilip Prasad , Gorazd Medic , Georgi Kalitzin , Dmytro Mykolayovych Voytovych
Abstract: A compressor for use in a gas turbine engine including: an airfoil configured to rotate about an engine central longitudinal axis of the gas turbine engine; a casing, the casing including a radially inward surface; and a groove located within the casing opposite the airfoil, the groove is recessed in a radially outward direction from the radially inward surface of the casing, wherein the groove is defined by a forward groove wall, an aft groove wall opposite the forward groove wall, and a base groove interposed between the forward groove wall and the aft groove wall, and wherein the forward groove wall is operably shaped to generate an aft directed jet.
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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：US20200332673A1
公开(公告)日：2020-10-22
申请号：US16388199
申请日：2019-04-18
Applicant: United Technologies Corporation
Inventor： Michael M. Joly , Andrzej Ernest Kuczek , Zaffir A. Chaudhry , Gorazd Medic , Dilip Prasad
Abstract: A gas turbine engine includes a plurality of blades circumferentially spaced from each other. A plurality of rings are spaced radially outward from the plurality of blade. At least one actuator is in mechanical communication with the plurality of rings for moving the plurality of rings in an axial direction to create an axial gap adjacent at least one of the plurality of rings.
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公开(公告)号：US11092030B2
公开(公告)日：2021-08-17
申请号：US16388199
申请日：2019-04-18
Applicant: United Technologies Corporation
Inventor： Michael M. Joly , Andrzej Ernest Kuczek , Zaffir A. Chaudhry , Gorazd Medic , Dilip Prasad
Abstract: A gas turbine engine includes a plurality of blades circumferentially spaced from each other. A plurality of rings are spaced radially outward from the plurality of blade. At least one actuator is in mechanical communication with the plurality of rings for moving the plurality of rings in an axial direction to create an axial gap adjacent at least one of the plurality of rings.
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