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

IPC: F01D17/16 ,  F01D9/04 ,  F01D17/24 ,  F02C9/22

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.

公开(公告)号：US11028725B2

公开(公告)日：2021-06-08

申请号：US16219240

申请日：2018-12-13

Applicant: United Technologies Corporation

Inventor： Zaffir A. Chaudhry ,  Andrzej Ernest Kuczek ,  Dilip Prasad

IPC: F01D17/12

Abstract: A morphing aerodynamic control surface geometry comprising a control surface having an articulated portion comprising a flexible skin coupled at an exterior of the articulated portion, the flexible skin comprising opposed interlocking elements sandwiched within a flexible polymer coupled to the interlocking elements; wherein the flexible skin is configured compliant responsive to an articulation of the articulated portion.

公开(公告)号：US10961911B2

公开(公告)日：2021-03-30

申请号：US15407586

申请日：2017-01-17

Applicant: United Technologies Corporation

Inventor： Matthew E. Bintz ,  Dilip Prasad

IPC: F02C7/18 ,  F01D25/12 ,  F04D27/02 ,  F02C6/08 ,  F01D5/08

Abstract: A gas turbine engine includes an engine core having a compressor section, a combustor fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor section. At least one compressor bleed connects a compressor flowpath with a first cooled cooling air path. The first cooled cooling air path includes a supplementary coolant injector connected to a supplementary coolant supply. The cooled cooling air path including a portion exterior to the engine core.

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

IPC: F01D17/16 ,  F01D17/24 ,  F01D9/04

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.

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

IPC: F01D11/10 ,  F02C7/28

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.

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

IPC: F01D5/14 ,  B64D27/14 ,  B64D33/02

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.

公开(公告)号：US20180258857A1

公开(公告)日：2018-09-13

申请号：US15452634

申请日：2017-03-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dilip Prasad ,  Bruce L. Morin

IPC: F02C7/045 ,  F01D25/06

CPC classification number: F02C7/045 ,  B64D2033/0206 ,  F01D25/06 ,  F02K1/827 ,  F02K3/06 ,  F05D2260/96 ,  F05D2260/963 ,  G10K11/172 ,  Y02T50/672

Abstract: Disclosed is a flutter damper including a first plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a first fan flutter mode, the first plurality of chambers in fluid communication with a flow surface, and a second plurality of chambers configured for peak acoustical energy absorption at a frequency range that is associated with a second fan flutter mode, the second plurality of chambers in fluid communication with the flow surface, and wherein the first plurality of chambers and second plurality of chambers are disposed in a grid pattern.