公开(公告)号：US11255197B2

公开(公告)日：2022-02-22

申请号：US16734464

申请日：2020-01-06

Applicant: United Technologies Corporation

Inventor： Jason Shenny ,  Jeffrey T. Morton ,  Alberto A. Mateo ,  San Quach ,  Gregory Anselmi

IPC: F01D5/18 ,  F04D29/32 ,  F04D29/58

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that has an internal wall and an external wall. The external wall defines pressure and suction sides that extends in a chordwise direction between a leading edge and a trailing edge, a first impingement cavity and a second impingement cavity bounded by the external wall at a leading edge region that defines the leading edge. A first crossover passage within the internal wall is connected to the first impingement. The first crossover passage defines a first passage axis that intersects a surface of the first impingement cavity. A second crossover passage within the internal wall is connected to the second impingement cavity. The second crossover passage defines a second passage axis that intersects a surface of the second impingement cavity.

公开(公告)号：US11255026B2

公开(公告)日：2022-02-22

申请号：US16415466

申请日：2019-05-17

Applicant: United Technologies Corporation

Inventor： Bart A. van Hassel

IPC: D01D10/02 ,  D01F9/08 ,  D02J13/00 ,  C04B41/00 ,  C04B41/80 ,  D01D5/00 ,  D01F9/10 ,  D06M10/00 ,  C04B37/00 ,  C04B35/622

Abstract: A method for forming an ultra-high temperature (UHT) composite structure includes dispensing a polymeric precursor with a spinneret biased at a first DC voltage; forming a plurality of nanofibers from the polymeric precursor; receiving the plurality of nanofibers with a collector biased at a second DC voltage different than the first DC voltage; and changing a direction of movement of the plurality of nanofibers between the spinneret and the collector with a plurality of magnets having a magnetic field by adjusting the magnetic field.

公开(公告)号：US11248989B2

公开(公告)日：2022-02-15

申请号：US16448365

申请日：2019-06-21

Applicant: United Technologies Corporation

Inventor： Nagendra Somanath ,  Justin R. Urban ,  Michael J. Giering ,  Quan Long ,  Alexandria Dorgan

IPC: G01M15/14 ,  B64F5/60 ,  F02D35/02

Abstract: A system for providing real time aircraft engine sensor analysis includes a computer system configured to receive an engine operation data set in real time. The computer system includes a machine learning based analysis tool and a user interface configured to display a real time analysis of the engine operation data set. The user interface includes at least one portion configured to identify a plurality of anomalies in the engine operation data set.

公开(公告)号：US11248791B2

公开(公告)日：2022-02-15

申请号：US15889764

申请日：2018-02-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven D Porter ,  Jon E Sobanski

IPC: F23R3/06 ,  B22C7/02 ,  F01D25/12 ,  F23R3/00 ,  B22D25/02 ,  F23R3/50 ,  F02K1/82 ,  F02C7/24 ,  F02K3/06

Abstract: A heat shield panel for a gas turbine engine combustor is disclosed. The heat shield panel includes a hot side defining a first surface having an outer perimeter, a cold side defining a second surface spaced from the first surface and a plurality of holes, each hole including a central axis having vector components defined by a common vector.

公开(公告)号：US11248523B2

公开(公告)日：2022-02-15

申请号：US16676112

申请日：2019-11-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nicholas D. Leque ,  Joseph H. Polly

IPC: F02C7/36 ,  F02C3/113 ,  F16H37/02 ,  F16H63/02

Abstract: A power extraction system for a gas turbine engine may comprise a low spool transmission and a low spool accessory gearbox. The low spool accessory gearbox may comprise a generator and a dual clutch transmission. The dual clutch transmission may be coupled between the low spool transmission and the generator.

公开(公告)号：US11248470B2

公开(公告)日：2022-02-15

申请号：US16594402

申请日：2019-10-07

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley ,  Allan N. Arisi

IPC: F01D5/18 ,  F01D5/20

Abstract: An airfoil includes an airfoil section that has an airfoil wall that define leading and trailing ends and first and second sides that join the leading and trailing ends. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. The airfoil section extends form a platform. The platform defines a shelf that extends forward from the first end at the leading end of the airfoil section to a platform leading edge, aft from the first end at the trailing end of the airfoil section to a platform trailing edge, laterally from the first end at the first side of the airfoil section to a first platform side edge, and laterally from the first end at the second side of the airfoil section to a second platform side edge. The internal core cavity extends from the airfoil section into the shelf.

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

IPC: F01D25/24 ,  B33Y10/00 ,  B33Y80/00

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.

公开(公告)号：US11242768B2

公开(公告)日：2022-02-08

申请号：US16815042

申请日：2020-03-11

Applicant: United Technologies Corporation

Inventor： Tracy A. Propheter-Hinckley

IPC: F01D25/12 ,  F01D25/14 ,  F01D25/24

Abstract: A gas turbine engine article includes an article wall that defines a cavity, a cooling passage network embedded between inner and outer portions of the article wall, and at least one conical passage through at least a portion of the inner portion of the article wall. The cooling passage network has an inlet orifice through the inner portion of the article wall to receive cooling air from the cavity, an outlet orifice through the outer portion of the article wall, and an intermediate region of passages that connects the inlet orifice to the outlet orifice. The conical passage has a first end that is proximate the cavity and a second end that opens at the intermediate region of passages.

公开(公告)号：US11236677B2

公开(公告)日：2022-02-01

申请号：US16413347

申请日：2019-05-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Matthew Andrew Hough ,  John S. Tu ,  Stephen C. Harmon ,  Paul F. Croteau ,  Russell B. Hanson ,  Joshua C. Rathgeb

IPC: F02C7/28 ,  F02C7/32

Abstract: A diffuser case support structure for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case. A sliding joint is formed between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing.

公开(公告)号：US11236619B2

公开(公告)日：2022-02-01

申请号：US16404774

申请日：2019-05-07

Applicant: United Technologies Corporation

Inventor： Daniel A. Bales ,  Michael DuPont ,  Eric W. Malmborg

IPC: B23K1/00 ,  F01D5/00 ,  F01D5/18 ,  B23K101/00

Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil body extending between leading and trailing edges in a chordwise direction and extending from a root section in a spanwise direction, and the airfoil body defining pressure and suction sides separated in a thickness direction. The airfoil body defines a recessed region extending inwardly from at least one of the pressure and suction sides, and the airfoil body includes one or more ribs that define a plurality of pockets within a perimeter of the recessed region. A plurality of cover skins is welded to the airfoil body along the one or more ribs to enclose respective ones of the plurality of pockets. The plurality of cover skins formed from a common cover having a perimeter that is dimensioned to mate with the perimeter of the recess. A method of forming a gas turbine engine component is also disclosed.