公开(公告)号：US20240344744A1

公开(公告)日：2024-10-17

申请号：US18755138

申请日：2024-06-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Wei Xie ,  Subramanyaravi Annapragada ,  Joseph V. Mantese ,  Parmesh Verma ,  Thomas D. Radcliff

IPC: F25B21/00 ,  B29C41/00 ,  B29C41/12 ,  B29L7/00 ,  H10N15/10

CPC classification number: F25B21/00 ,  B29C41/003 ,  B29C41/12 ,  H10N15/15 ,  B29K2995/0003 ,  B29L2007/008 ,  F25B2321/001 ,  Y02B30/00

Abstract: A method of making an electrocaloric element includes dissolving or dispersing an electrocaloric polymer in an organic solvent having a boiling point of less than 100° C. at 1 atmosphere to form a liquid composition comprising the electrocaloric polymer. A film of the liquid composition is cast on a substrate, and the organic solvent is evaporated to form a film of the electrocaloric polymer. The film is removed from the substrate and disposed between electrical conductors to form an electrocaloric element.

公开(公告)号：US12106235B2

公开(公告)日：2024-10-01

申请号：US16360480

申请日：2019-03-21

Applicant: United Technologies Corporation

Inventor： Sharath B. Nagaraja ,  Mathew R. Greco

IPC: G06Q10/04 ,  B64F5/60 ,  G05B23/02 ,  G06F18/25 ,  G06N3/04 ,  G08G5/00 ,  H04W4/029

CPC classification number: G06Q10/04 ,  B64F5/60 ,  G05B23/0281 ,  G05B23/0283 ,  G06F18/25 ,  G06N3/04 ,  G08G5/0026 ,  G08G5/0039 ,  G08G5/006 ,  H04W4/029

Abstract: A method for forecasting aircraft engine deterioration includes creating a first fused data set corresponding to a first actual aircraft engine. The first fused data set includes at least one as manufactured parameter of the actual aircraft engine, expected operating parameters of the first actual aircraft engine, and actual operating parameters of the actual aircraft engine. The actual operating parameters of the actual aircraft engine include internal aircraft sensor data, and external flight tracking data. The method further includes predicting an expected engine deterioration of the first actual engine based on the expected operating parameters and the actual operating parameters of the first actual aircraft engine by applying the first fused data set to a forecasting model. The forecasting model is a recurrent neural network based algorithm, and the recurrent neural network based algorithm is trained via a plurality of second fused data sets corresponding to actual aircraft engines.

公开(公告)号：US12000305B2

公开(公告)日：2024-06-04

申请号：US16682453

申请日：2019-11-13

Applicant: United Technologies Corporation

Inventor： Brandon W. Spangler ,  David R. Pack

IPC: F01D5/18

CPC classification number: F01D5/189 ,  F05D2220/32 ,  F05D2250/75 ,  F05D2260/201 ,  F05D2260/22141

Abstract: An airfoil includes an airfoil wall that defines a leading end, a trailing end, a pressure side, a suction side, and a mean line. First and second ribs each connect the pressure side and the suction side. Each of the first and second ribs define a tube portion that circumscribes a rib passage, and first and second connector arms that solely join the tube portion to, respectively, the pressure side and the suction side. The first rib, the second rib, and the airfoil wall bound a continuous cooling channel there between. The continuous cooling channel has a pressure side portion to the pressure side of the mean line and a suction side portion to the suction side of the mean line. The pressure side portion and the suction side portion each have a cross-sectioned shape selected from an L-shape, a T-shape, and an l-shape.

公开(公告)号：US11970972B2

公开(公告)日：2024-04-30

申请号：US16661459

申请日：2019-10-23

Applicant: United Technologies Corporation

Inventor： Andrew V. Schwendenmann ,  Todd A. Davis ,  Ryan Lureau ,  Reade W. James

IPC: F02C7/06 ,  F16C33/66

CPC classification number: F02C7/06 ,  F16C33/6685 ,  F05D2220/32 ,  F05D2240/50 ,  F05D2260/98 ,  F16C2360/23

Abstract: A scupper suitable for a bearing compartment of a gas turbine engine includes a windage blocker in a gutter section upstream of a drain hole, the windage blocker extends from a wall of the gutter section. A method for capturing wept oil in a bearing compartment of a gas turbine engine includes positioning a windage blocker adjacent to a drain hole forming a passage space and increasing a pressure upstream of the windage blocker to generate a vortex downstream of the windage blocker creating an oil re-circulation zone promoting oil drainage into the drain hole.

公开(公告)号：US11921490B2

公开(公告)日：2024-03-05

申请号：US16743528

申请日：2020-01-15

Applicant: United Technologies Corporation

Inventor： Steven W. Burd

IPC: G05B19/4099 ,  B22F5/00 ,  B22F7/06 ,  B22F10/25 ,  B22F10/28 ,  B29C64/386 ,  B29C64/40 ,  B33Y10/00 ,  B33Y50/00 ,  B33Y50/02

CPC classification number: G05B19/4099 ,  B22F5/009 ,  B22F7/062 ,  B22F10/28 ,  B29C64/386 ,  B29C64/40 ,  B33Y10/00 ,  B33Y50/00 ,  B22F10/25 ,  B33Y50/02 ,  G05B2219/35134 ,  G05B2219/49007 ,  G05B2219/49014 ,  Y02P10/25

Abstract: An additive manufacturing method includes segmenting a CAD file of a component along a build interface to define at least a first component segment and a second component segment, each of the first component segment and the second component segment sized to fit within an additive manufacturing build chamber; additive manufacturing the first component segment and the second component segment within the build chamber; and bonding the first component segment and the second component segment to form the component.

公开(公告)号：US11866380B2

公开(公告)日：2024-01-09

申请号：US16536629

申请日：2019-08-09

Applicant: United Technologies Corporation

Inventor： Imelda P. Smyth ,  Sarah A. Frith

IPC: C04B41/50 ,  C04B41/45 ,  C04B35/565

CPC classification number: C04B41/5066 ,  C04B35/565 ,  C04B41/4527 ,  C04B41/4543 ,  C04B41/5024 ,  C04B41/5042 ,  C04B41/5059

Abstract: A method of fabricating a coating includes providing a ceramic matrix composite that includes SiC fibers disposed in a SiC matrix, depositing a base slurry on the ceramic matrix composite, wherein the base slurry contains powders of a metal oxide, at least one of silicon carbide, silicon nitride, or free silicon, and barium-magnesium-aluminosilicate in a first carrier fluid, drying the deposited base slurry to produce a base green layer, depositing a transition slurry on the base green layer, wherein the transition slurry contains powders of a metal oxide, at least one of silicon carbide, silicon nitride, or free silicon, at least one of zirconium carbide, zirconium nitride, or zirconium oxide, and barium-magnesium-aluminosilicate in a second carrier fluid, drying the deposited transition slurry to produce a transition green layer, and forming a consolidated coating on the ceramic matrix composite by heating the base green layer and the at least one transition green layer to cause chemical reactions that convert the powders to metal-silicon-oxygen rich phase and metal-zirconium-oxygen rich phase.

公开(公告)号：US11808529B2

公开(公告)日：2023-11-07

申请号：US16271267

申请日：2019-02-08

Applicant: United Technologies Corporation

Inventor： Michael A. Disori ,  Steven J. Bullied ,  Ryan C. Breneman ,  John Marcin ,  David J. Hyland ,  William P. Stillman ,  Carl R. Verner

IPC: F28F1/26 ,  B22D27/04

CPC classification number: F28F1/26 ,  B22D27/045

Abstract: A cast part includes an outermost wall, at least one inner wall defining at least two internal passages and at least one cast cooling fin extending from an outer surface. The cooling fin includes a ratio of fin height to an average fin thickness that is greater than 2.0 and no more than 18.0. A method is also disclosed.

公开(公告)号：US11753944B2

公开(公告)日：2023-09-12

申请号：US16594353

申请日：2019-10-07

Applicant: United Technologies Corporation

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

IPC: F01D5/18 ,  F01D25/12 ,  F02C7/18

CPC classification number: F01D5/186 ,  F01D5/187 ,  F01D25/12 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/201 ,  F05D2260/204

Abstract: An airfoil section has an airfoil wall that defines a leading end, a trailing end, and first and second sides that join the leading end and the trailing end. The airfoil wall circumscribes an internal core cavity. A skincore passage is embedded in the first side of the airfoil wall between inner and outer portions of the first side of airfoil wall. The skincore passage defines a passage forward edge and a passage aft edge. The first side of the airfoil wall has a portion that tapers in thickness at the passage aft edge. A cooling passage is embedded in the second side of the airfoil wall between inner and outer portions of the second side of airfoil wall. The inner portion of the second side of the airfoil wall includes a protrusion located across the internal core cavity from the portion of the first side that tapers in thickness.

公开(公告)号：US11702950B2

公开(公告)日：2023-07-18

申请号：US16388219

申请日：2019-04-18

Applicant: United Technologies Corporation

Inventor： John R. Farris ,  Michael G. McCaffrey

IPC: F01D11/12 ,  B05D3/00 ,  F01D25/00 ,  C23C4/01 ,  C23C28/04 ,  C23C4/18 ,  C23C4/11

CPC classification number: F01D11/12 ,  B05D3/007 ,  C23C4/01 ,  C23C4/11 ,  C23C4/18 ,  C23C28/042 ,  F01D11/122 ,  F01D25/005 ,  F05D2240/11 ,  F05D2250/294 ,  F05D2300/20 ,  Y02T50/60

Abstract: A method of forming a coating includes disposing a substrate having a plurality of protrusions on a seal and layering a topcoat over the protrusions. The method of forming a coating also includes creating a wear pattern and converting the topcoat. A turbine section includes a casing, a plurality of blades within the casing, and a substrate deposited on the casing having a plurality of protrusions. The turbine also includes an unconverted topcoat disposed over the plurality of protrusions, the topcoat having segmented portions defining a plurality of faults extending from the protrusions through the topcoat. A method of forming a coating includes creating a channel in the coating during an initial rub event and converting the coating during a high-temperature event. Converting the coating includes preserving the channel created during the initial rub event.

公开(公告)号：US11692582B2

公开(公告)日：2023-07-04

申请号：US16270963

申请日：2019-02-08

Applicant: United Technologies Corporation

Inventor： Kevin M. Brown ,  Paul R. Senofonte ,  Felix Izquierdo

IPC: F16B21/00 ,  F16B39/10 ,  F16B21/16

CPC classification number: F16B39/10 ,  F16B21/16

Abstract: A fastener system for securing a component to a structure is provided. The system includes a pin portion and a clip portion. The pin portion has a head and a shaft. The clip portion has a head engagement flange and a retainer flange configured to receive a fastener that extends along a first axis. The clip portion and the pin portion are configured for engagement with one another in an engaged position, and in the engaged position the pin portion shaft extends along a second axis non-parallel to the first axis.