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公开(公告)号：US20210332713A1
公开(公告)日：2021-10-28
申请号：US16856752
申请日：2020-04-23
Inventor： Keith Sadler , Ted J. Freeman , Aaron D. Sippel , Alexandra Baucco
Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
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公开(公告)号：US11346234B2
公开(公告)日：2022-05-31
申请号：US16732960
申请日：2020-01-02
Applicant: Rolls-Royce plc
Inventor： Keith Sadler , Michael J. Whittle
Abstract: A turbine vane assembly includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The turbine vanes are adapted to interact with gases flowing through a gas path of the gas turbine engine. The outer vane support is arranged radially outward of the turbine vane and configured to receive aerodynamic loads from the turbine vanes. The inner vane support is arranged radially inward from the outer vane support to locate the turbine vane assembly therebetween.
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公开(公告)号：US11208911B2
公开(公告)日：2021-12-28
申请号：US16856752
申请日：2020-04-23
Inventor： Keith Sadler , Ted J. Freeman , Aaron D. Sippel , Alexandra Baucco
Abstract: An assembly adapted for use in a gas turbine engine includes a carrier and a blade track segment. The carrier extends at least partway about an axis. The blade track segment is supported by the carrier radially relative to the axis to define a portion of a gas path of the assembly.
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公开(公告)号：US20210207486A1
公开(公告)日：2021-07-08
申请号：US16732960
申请日：2020-01-02
Applicant: Rolls-Royce plc
Inventor： Keith Sadler , Michael J. Whittle
Abstract: A turbine vane assembly includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The turbine vanes are adapted to interact with gases flowing through a gas path of the gas turbine engine. The outer vane support is arranged radially outward of the turbine vane and configured to receive aerodynamic loads from the turbine vanes. The inner vane support is arranged radially inward from the outer vane support to locate the turbine vane assembly therebetween.
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5.发明申请公开(公告)号：US20210140333A1
公开(公告)日：2021-05-13
申请号：US16679869
申请日：2019-11-11
Inventor： Michael J. Whittle , Keith Sadler , Ted J. Freeman
Abstract: A turbine assembly for use with a gas turbine engine includes a bladed wheel assembly, a vane assembly, and an inner seal. The bladed wheel assembly is adapted to interact with gases flowing through a gas path of the gas turbine engine. The vane assembly is located upstream of the bladed wheel assembly and adapted to direct the gases at the bladed wheel assembly. The inner seal is configured to block gases from passing around the vane assembly.
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Patent Agency Ranking
公开(公告)号：US11415007B2
公开(公告)日：2022-08-16
申请号：US16752183
申请日：2020-01-24
Applicant: Rolls-Royce plc
Inventor： Michael J. Whittle , Keith Sadler , Matthew D. Thomason , Andrew Holt
Abstract: A gas turbine engine includes a shroud ring, a vane ring, and a secondary flow assembly. The shroud ring extends around an associated turbine wheel and includes a carrier segment and a blade track segment comprising ceramic matrix composite materials. The blade track segment and the carrier segment defining a shroud cavity radially therebetween. The vane ring includes a heat shield comprising ceramic matrix composite materials that forms an outer platform, an inner platform, and an airfoil defining a heat shield cavity radially through the heat shield. The secondary flow assembly includes a recirculating flow circuit having a discharge tube and a vane pressurizing tube; and the secondary flow assembly is configured to cool the blade track segment. The flow circuit is further configured to pressurize the heat shield cavity thereby providing a seal against the gases from the primary gas path entering the heat shield cavity.
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公开(公告)号：US11415005B2
公开(公告)日：2022-08-16
申请号：US17065948
申请日：2020-10-08
Applicant: Rolls-Royce plc
Inventor： Michael J. Whittle , Keith Sadler
Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a plurality of turbine vanes, an outer vane support, and an inner vane support. The plurality of turbine vanes comprise ceramic matrix composite material and are adapted to interact with hot gases flowing through a gas path of the gas turbine engine during use of the turbine vane assembly.
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公开(公告)号：US20210231022A1
公开(公告)日：2021-07-29
申请号：US16752183
申请日：2020-01-24
Applicant: Rolls-Royce plc
Inventor： Michael J. Whittle , Keith Sadler , Matthew D. Thomason , Andrew Holt
Abstract: A gas turbine engine includes a shroud ring, a vane ring, and a secondary flow assembly. The shroud ring extends around an associated turbine wheel and includes a carrier segment and a blade track segment comprising ceramic matrix composite materials. The blade track segment and the carrier segment defining a shroud cavity radially therebetween. The vane ring includes a heat shield comprising ceramic matrix composite materials that forms an outer platform, an inner platform, and an airfoil defining a heat shield cavity radially through the heat shield. The secondary flow assembly includes a recirculating flow circuit having a discharge tube and a vane pressurizing tube; and the secondary flow assembly is configured to cool the blade track segment. The flow circuit is further configured to pressurize the heat shield cavity thereby providing a seal against the gases from the primary gas path entering the heat shield cavity.
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9.发明授权公开(公告)号：US11504813B2
公开(公告)日：2022-11-22
申请号：US16876834
申请日：2020-05-18
Inventor： Michael J. Whittle , Stephen Harris , Keith Sadler , Matthew D. Thomason , Andrew Norton , James Kell
Abstract: A method comprises inspecting a ceramic matrix composite component assembled in a gas turbine engine to determine an extent of damage to the ceramic matrix composite component, determining a repair technique to repair the damage to the ceramic matrix composite component based on the extent of damage to the ceramic matrix composite component, and repairing the ceramic matrix composite component using the repair technique.
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10.发明授权公开(公告)号：US11415016B2
公开(公告)日：2022-08-16
申请号：US16679869
申请日：2019-11-11
Inventor： Michael J. Whittle , Keith Sadler , Ted J. Freeman
Abstract: A turbine assembly for use with a gas turbine engine includes a bladed wheel assembly, a vane assembly, and an inner seal. The bladed wheel assembly is adapted to interact with gases flowing through a gas path of the gas turbine engine. The vane assembly is located upstream of the bladed wheel assembly and adapted to direct the gases at the bladed wheel assembly. The inner seal is configured to block gases from passing around the vane assembly.
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