公开(公告)号：US11994089B2

公开(公告)日：2024-05-28

申请号：US16837143

申请日：2020-04-01

Applicant: United Technologies Corporation

Inventor： Dmitriy B. Sidelkovskiy ,  Pitchaiah Vijay Chakka ,  Michael Winter ,  Daniel Bernard Kupratis

IPC: F02K3/06 ,  F04D29/32 ,  F01D17/16 ,  F02C7/36

CPC classification number: F02K3/06 ,  F04D29/323 ,  F01D17/162 ,  F02C7/36 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2260/40311 ,  F05D2260/74 ,  F05D2260/79

Abstract: An after-fan system for a gas turbine engine includes a variable pitch fan exit guide vane array. An after-fan turbine downstream of the variable pitch fan exit guide vane array and a control operable to vary a pitch of the variable fan exit guide vane array. A method of generating thrust for a gas turbine engine includes rotating a fan section with an array of fan blades; rotating an after-fan turbine downstream of the fan section; and varying a pitch of a variable fan exit guide vane array downstream of the fan section and upstream of the after-fan turbine.

公开(公告)号：US10738694B1

公开(公告)日：2020-08-11

申请号：US16110473

申请日：2018-08-23

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Dmitriy B. Sidelkovskiy ,  Neil Terwilliger ,  William G. Sheridan

IPC: F02C3/067 ,  F02K3/06 ,  F02C7/32 ,  F02K3/072 ,  B64D27/02

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible things, a fan including a plurality of fan blades rotatable about an axis, a plurality of inlet guide vanes mounted forward of the plurality of fan blades, the plurality of inlet guide vanes selectively rotatable about the axis independent of the plurality of fan blades; and a motor for controlling rotation of the plurality of inlet guide vanes about the axis.

公开(公告)号：US20200248628A1

公开(公告)日：2020-08-06

申请号：US16263268

申请日：2019-01-31

Applicant: United Technologies Corporation

Inventor： Dmitriy B. Sidelkovskiy ,  James Evans

IPC: F02C7/30

Abstract: Core housings for gas turbine engines are described. The core housings include a housing surface defining an exterior surface of the core housing, a housing aperture arranged on the housing surface, the housing aperture configured to enable fluid communication between an external environment and an interior of the core housing, a drainage hole arranged upstream relative to the housing aperture, the drainage hole configured to enable draining of a fluid from an interior of the core housing to the external environment, and a redirection device arranged to receive a fluid from the drainage hole and direct such fluid away from the housing aperture.

公开(公告)号：US10450898B2

公开(公告)日：2019-10-22

申请号：US14621456

申请日：2015-02-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dmitriy B. Sidelkovskiy ,  Steven H. Zysman ,  Robert E. Malecki

IPC: B64D29/06 ,  F01D25/28 ,  B64D29/00 ,  F02K1/52 ,  F02K1/72 ,  F02C7/20 ,  F01D25/24

Abstract: The present disclosure relates generally to an aerodynamic track fairing assembly used on an engine nacelle, the track fairing assembly positionable on the aft section of the engine nacelle, the aerodynamic track fairing assembly including: an upper section extending toward an aft end of the aft section of the engine nacelle; a bottom section extending toward the aft end of the aft section of the engine nacelle, the bottom section affixed to the upper section to form a track cavity therebetween; and a fairing fitting disposed within the track cavity and affixed to the bottom section.

公开(公告)号：US11046445B2

公开(公告)日：2021-06-29

申请号：US15660687

申请日：2017-07-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dmitriy B. Sidelkovskiy ,  Steven H. Zysman

IPC: B64D29/00 ,  B64D27/18 ,  B64D29/02 ,  B64D33/04 ,  F02C3/04 ,  F02K1/72 ,  B64D33/02 ,  F02K3/06

Abstract: A nacelle may comprise an inlet cowling comprising an inlet cowling aft edge having an aft edge length; a boat tail cowling comprising a boat tail cowling forward edge having a forward edge length, wherein the boat tail cowling forward edge is disposed adjacent to the inlet cowling aft edge. The forward edge length may be shorter than the aft edge length, forming a step being defined by a portion of the inlet cowling aft edge that is radially outward of the boat tail cowling forward edge. The nacelle may further comprise a transition fairing coupled to the boat tail cowling, wherein the transition fairing comprises a fairing forward edge disposed adjacent to the inlet cowling aft edge and a fairing ramp surface spanning between the inlet cowling aft edge and a boat tail cowling external surface.

公开(公告)号：US20200063657A1

公开(公告)日：2020-02-27

申请号：US16550576

申请日：2019-08-26

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Dmitriy B. Sidelkovskiy ,  Neil Terwilliger ,  William G. Sheridan

IPC: F02C3/067 ,  F02K3/06 ,  F02C7/32 ,  F02K3/072

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible things, a fan including a plurality of fan blades rotatable about an axis, a plurality of inlet guide vanes mounted forward of the plurality of fan blades, the plurality of inlet guide vanes selectively rotatable about the axis independent of the plurality of fan blades; and a motor for controlling rotation of the plurality of inlet guide vanes about the axis.

公开(公告)号：US10422280B2

公开(公告)日：2019-09-24

申请号：US15452614

申请日：2017-03-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dmitriy B. Sidelkovskiy ,  Bruce L. Morin ,  David A. Anderson

IPC: F02C7/045 ,  F02K1/82 ,  B64D33/02

Abstract: A flutter damper is disclosed, which includes a chamber configured to fluidly communicate with a gas flow, the chamber being filled with an open celled foam bulk damper, and wherein the chamber is configured for peak acoustical energy absorption at a frequency range that is associated with one or more fan flutter modes.

公开(公告)号：US20210262359A1

公开(公告)日：2021-08-26

申请号：US16797194

申请日：2020-02-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dmitriy B. Sidelkovskiy ,  Pitchaiah Vijay Chakka ,  Michael Winter ,  Daniel Bernard Kupratis ,  Nathan L. Messersmith

IPC: F01D15/10 ,  F02C6/06 ,  F01D15/12 ,  H02K7/116 ,  H02K7/18 ,  H02K7/20 ,  H02K11/00 ,  B64D27/10 ,  B64D27/24 ,  B64D41/00

Abstract: An after-fan system for an engine may comprise an after-fan turbine an electrical generator operationally coupled to the after-fan turbine, and an electric motor electrically coupled to the electrical generator. The electrical generator may be configured to generate an electrical current in response to rotation of the after-fan turbine. The electric motor may be configured to generate torque.

公开(公告)号：US11028779B2

公开(公告)日：2021-06-08

申请号：US16263268

申请日：2019-01-31

Applicant: United Technologies Corporation

Inventor： Dmitriy B. Sidelkovskiy ,  James Evans

IPC: F01D25/24 ,  F02C7/30 ,  F01D25/32

Abstract: Core housings for gas turbine engines are described. The core housings include a housing surface defining an exterior surface of the core housing, a housing aperture arranged on the housing surface, the housing aperture configured to enable fluid communication between an external environment and an interior of the core housing, a drainage hole arranged upstream relative to the housing aperture, the drainage hole configured to enable draining of a fluid from an interior of the core housing to the external environment, and a redirection device arranged to receive a fluid from the drainage hole and direct such fluid away from the housing aperture.

公开(公告)号：US10371092B2

公开(公告)日：2019-08-06

申请号：US14817611

申请日：2015-08-04

Applicant: United Technologies Corporation

Inventor： Dmitriy B. Sidelkovskiy ,  Oleg Petrenko ,  Robert E. Malecki ,  Steven H. Zysman

IPC: F02K1/78 ,  B64D29/00 ,  F02K1/40 ,  F02K1/52 ,  F02K1/00 ,  F02K1/82 ,  F02K1/36 ,  F02K3/077 ,  F02C3/04 ,  F02K3/06 ,  B64D29/02 ,  B64D29/04

Abstract: A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.