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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
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.
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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
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.
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公开(公告)号：US11156101B2
公开(公告)日：2021-10-26
申请号：US16858955
申请日：2020-04-27
Applicant: United Technologies Corporation
Inventor： San Quach , Tracy A. Propheter-Hinckley , Steven Bruce Gautschi
Abstract: A component for a gas turbine engine includes, among other things, an airfoil that includes a pressure sidewall and a suction sidewall that meet together at both a leading edge and a trailing edge, the airfoil extending radially from a platform to a tip, a tip pocket formed in the tip and terminating prior to the trailing edge, and one or more heat transfer augmentation devices formed in the tip pocket.
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公开(公告)号：US11118474B2
公开(公告)日：2021-09-14
申请号：US15727816
申请日：2017-10-09
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Tracy A. Propheter-Hinckley , Raymond Surace
Abstract: A vane platform cooling system may comprise a combustor shell and a combustor panel. A cavity may be located between the combustor shell and the combustor panel. A surface of the cavity may be angled toward the combustor shell. An orifice may be formed in a vane platform located aft of the combustor panel. A standoff located in the cavity may direct air toward the vane platform. An aperture may be formed in a surface of the vane platform. A channel formed through the vane platform may connect the orifice and aperture.
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公开(公告)号：US11028702B2
公开(公告)日：2021-06-08
申请号：US16218691
申请日：2018-12-13
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Allan N. Arisi
Abstract: An airfoil includes a cooling passage network is embedded in an airfoil wall between inner and outer portions of the airfoil wall. The cooling passage network has an entrance region adjacent the first end of the airfoil section, a plenum region between the entrance region and the second end of the airfoil section, and an exit region adjacent the plenum region. The entrance region includes a plurality of flow guides that divide the entrance region into a plurality of channels that open into the plenum region. The plenum region includes a plurality of pedestals that have a shape that is different from the flow guides.
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Patent Agency Ranking
公开(公告)号：US20210148236A1
公开(公告)日：2021-05-20
申请号：US16667949
申请日：2019-10-30
Applicant: United Technologies Corporation
Inventor： Corneil S. Paauwe , Tracy A. Propheter-Hinckley , Allan N. Arisi
IPC: F01D5/18
Abstract: A gas turbine engine article includes an article wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The article wall defines a cavity. A cooling passage network is embedded in the article wall between inner and outer portions of the article wall. The network has an inlet orifice through the inner portion to receive cooling air from the cavity, a plurality of sub-passages, at least one outlet orifice that is connected to the sub-passage region, and a manifold region that has a plenum upstream of the sub-passages. The outer portion of the article wall has a sloped impingement surface located opposite the inlet orifice. The sloped impingement surface is angled to divert flow of cooling air from the inlet orifice toward the plenum.
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公开(公告)号：US11008979B2
公开(公告)日：2021-05-18
申请号：US16425016
申请日：2019-05-29
Applicant: United Technologies Corporation
Inventor： Michael G. McCaffrey , Tracy A. Propheter-Hinckley
Abstract: A passive centrifugal valve for a gas turbine engine. The passive centrifugal valve includes an inner section with a flow control inlet orifice, a cantilevered valve adjacent to the flow control inlet orifice, and an outer section with a seal land geometry that operates to at least partially support the cantilevered valve in response to a first centrifugal force that deflects the cantilevered valve away from the flow control inlet orifice.
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公开(公告)号：US10941663B2
公开(公告)日：2021-03-09
申请号：US15972637
申请日：2018-05-07
Applicant: United Technologies Corporation
Inventor： Timothy J. Jennings , Tracy A. Propheter-Hinckley , Kyle C. Lana
Abstract: Airfoils for gas turbine engines are provided. The airfoils include a body extending between leading and trailing edges in an axial direction, between pressure and suction sides in a circumferential direction, and between a root and tip in a radial direction. A first transitioning leading edge cavity is located adjacent one of the sides proximate the root of the body and transitions axially toward the leading edge as the first transitioning leading edge cavity extends radially toward the tip. A second transitioning leading edge cavity is adjacent the other side and adjacent the leading edge proximate the root of the body and transitions axially toward the trailing edge as the second transitioning leading edge cavity extends radially toward the tip. A portion of the second transitioning leading edge cavity shields a portion of the first transitioning leading edge cavity proximate the root of the body.
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公开(公告)号：US10890079B2
公开(公告)日：2021-01-12
申请号：US16208876
申请日：2018-12-04
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Justin M. Aniello , Kyle J. Brevick
Abstract: A gas turbine engine includes first and second arc segments that each have leading and trailing sides and first and second circumferential sides. The first circumferential side includes a first slot portion and the second circumferential side includes a second slot portion. The first and second slot portions are in registration and together define a seal slot. At least the first slot portion has a first concave arced back wall. A feather seal is entrapped in the seal slot and includes first and second feather seal circumferential sides. At least the first feather seal circumferential side has a first convex arced edge that is adjacent the first concave arced back wall of the first slot portion.
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公开(公告)号：US20200340405A1
公开(公告)日：2020-10-29
申请号：US16393205
申请日：2019-04-24
Applicant: United Technologies Corporation
Inventor： Tracy A. Propheter-Hinckley , Kyle J. Brevick
Abstract: A vane for a gas turbine engine includes at least one airfoil. A first platform has a first rail located at a first end of the airfoil. A second platform has a second rail located at a second end of the airfoil. A first chordal seal is located on an axially aft surface of the first rail. A second chordal seal is located on an aft surface of the second rail and has a second radius of curvature at least partially truncated by an outer edge of the second rail.
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