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公开(公告)号：US20230076312A1
公开(公告)日：2023-03-09
申请号：US17838032
申请日：2022-06-10
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jon E. Sobanski , Steven D. Porter
Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.
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公开(公告)号：US20210254553A1
公开(公告)日：2021-08-19
申请号：US17175087
申请日：2021-02-12
Applicant: Raytheon Technologies Corporation
Inventor： Caroline Karanian , Steven D. Porter , John T. Ols
Abstract: A brush seal system includes a component including a first mating surface. The brush seal system further includes a brush seal including a brush seal backing plate, a retaining ring, and a plurality of bristles retained between the brush seal backing plate and the retaining ring. The brush seal backing plate includes a second mating surface mounted to the first mating surface. The brush seal system further includes at least one cooling channel extending from an exterior side of the component to an interior side of the component so as to bypass the brush seal.
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公开(公告)号：US11041391B2
公开(公告)日：2021-06-22
申请号：US16852728
申请日：2020-04-20
Applicant: Raytheon Technologies Corporation
Inventor： Steven D. Porter , Shawn M. McMahon , Kevin Zacchera , Noah Wadsworth , Christopher Whitfield , Sean D. Bradshaw , Dennis M. Moura , David Bitzko , Alex J. Schneider
Abstract: A gas turbine engine includes a combustor. A turbine section is in fluid communication with the combustor. The turbine section includes a first vane stage aft of the combustor. A plurality of vane cooling passages extending through a forward flange of the first vane stage to the radial inner surface for communicating cooling airflow into the core flow path forward of the leading edge. A seal assembly is disposed between the combustor and the forward flange of the vane stage. The seal includes a plurality of circumferentially spaced apart slots and a plurality of seal cooling passages that extend from the radially outer surface to the radially inner surface at each of the plurality of circumferentially spaced apart slots.
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公开(公告)号：US11725816B2
公开(公告)日：2023-08-15
申请号：US17838032
申请日：2022-06-10
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jon E. Sobanski , Steven D. Porter
Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.
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公开(公告)号：US20210404659A1
公开(公告)日：2021-12-30
申请号：US17238021
申请日：2021-04-22
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Jon E. Sobanski , Steven D. Porter
Abstract: A heat shield panel for use in a gas turbine engine combustor is disclosed. In various embodiments, the heat shield panel includes a hot side, a cold side spaced from the hot side, a rail member disposed on the cold side proximate an outer perimeter, the rail member having an outer wall and an inner wall and an orifice extending through the rail member, from the inner wall to the outer wall, the orifice having an entrance portion having an entrance opening positioned on the inner wall and extending at least to an intermediate portion of the rail member and an exit portion having an exit opening positioned on the outer wall and extending at least to the intermediate portion of the rail member, the entrance portion of the orifice being angled relative to the exit portion of the orifice.
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Patent Agency Ranking
公开(公告)号：US11021980B2
公开(公告)日：2021-06-01
申请号：US16391544
申请日：2019-04-23
Applicant: Raytheon Technologies Corporation
Inventor： John T. Ols , Steven D. Porter
Abstract: A vane pack for a gas turbine engine includes an annular arrangement of vanes. A ring is secured around the vanes and extends proud of an axial end of the vanes.
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公开(公告)号：US20240003301A1
公开(公告)日：2024-01-04
申请号：US18130270
申请日：2023-04-03
Applicant: Raytheon Technologies Corporation
Inventor： Caroline Karanian , Steven D. Porter , John T. Ols
CPC classification number: F02C7/28 , F02C7/12 , F05D2220/32 , F05D2240/56 , F05D2260/20
Abstract: A brush seal system includes a component including a first mating surface. The brush seal system further includes a brush seal including a brush seal backing plate, a retaining ring, and a plurality of bristles retained between the brush seal backing plate and the retaining ring. The brush seal backing plate includes a second mating surface mounted to the first mating surface. The brush seal system further includes at least one cooling channel extending from an exterior side of the component to an interior side of the component so as to bypass the brush seal.
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公开(公告)号：US20220018285A1
公开(公告)日：2022-01-20
申请号：US16929220
申请日：2020-07-15
Applicant: Raytheon Technologies Corporation
Inventor： Nicholas Waters Oren , Steven D. Porter
Abstract: A multi-ring spacer includes a first ring having a first clocking position, a second ring coaxial with the first ring, and having a second clocking position. A total kink angle of the multi ring spacer is dependent on an angular deviation of the second ring's clocking position relative to the first ring's clocking position.
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公开(公告)号：US11959422B2
公开(公告)日：2024-04-16
申请号：US18130270
申请日：2023-04-03
Applicant: Raytheon Technologies Corporation
Inventor： Caroline Karanian , Steven D. Porter , John T. Ols
CPC classification number: F02C7/28 , F02C7/12 , F05D2220/32 , F05D2240/56 , F05D2260/20
Abstract: A brush seal system includes a component including a first mating surface. The brush seal system further includes a brush seal including a brush seal backing plate, a retaining ring, and a plurality of bristles retained between the brush seal backing plate and the retaining ring. The brush seal backing plate includes a second mating surface mounted to the first mating surface. The brush seal system further includes at least one cooling channel extending from an exterior side of the component to an interior side of the component so as to bypass the brush seal.
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公开(公告)号：US11619174B2
公开(公告)日：2023-04-04
申请号：US17175087
申请日：2021-02-12
Applicant: Raytheon Technologies Corporation
Inventor： Caroline Karanian , Steven D. Porter , John T. Ols
Abstract: A brush seal system includes a component including a first mating surface. The brush seal system further includes a brush seal including a brush seal backing plate, a retaining ring, and a plurality of bristles retained between the brush seal backing plate and the retaining ring. The brush seal backing plate includes a second mating surface mounted to the first mating surface. The brush seal system further includes at least one cooling channel extending from an exterior side of the component to an interior side of the component so as to bypass the brush seal.
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