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公开(公告)号：US20190078869A1
公开(公告)日：2019-03-14
申请号：US15702190
申请日：2017-09-12
Applicant: United Technologies Corporation
Inventor： Eli Cole Warren , Kevin A. Ford
Abstract: In combination a blade clearance sensor and a radial flow separation wall of a gas turbine engine is provided. The blade clearance sensor is embedded in the radial flow separation wall. The radial flow separation wall comprising: a splitter hoop located radially outward from blades in a first flow path of the gas turbine engine, the splitter hoop being about concentric to a blade path of the blades; and one or more guide vane bases attached to a guide vane located radially outward from the splitter hoop in a second flow path, each of the one or more guide vane bases being securely attached to a radially outward surface of the splitter hoop, wherein the blade clearance sensor is configured to detect a blade clearance between the blades and the splitter hoop.
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Patent Agency Ranking
公开(公告)号：US11686577B2
公开(公告)日：2023-06-27
申请号：US16137189
申请日：2018-09-20
Applicant: United Technologies Corporation
Inventor： Eli C. Warren , Kevin A. Ford , Patrick M. Harrington
CPC classification number: G01B21/16 , F01D21/003 , G01D11/16 , F01D21/04
Abstract: An angled face cap probe includes a housing having a radially inner end and a radially outer end, defining a cavity, and configured to be located radially outward from an airfoil. The angled face cap probe further includes a sensor located in the cavity at the radially inner end of the housing, having a sensor body with a sensing face that is angled to match or substantially match an angle of a radially outward face the airfoil, and having a sensor flat that is elongated in a first direction. The angled face cap probe further includes an outer cap located in the cavity, coupled to the housing, and having an outer cap main body and cap legs that extend radially inward from the outer cap main body to interface with the sensor flat to resist rotation of the sensor relative to the housing.
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公开(公告)号：US20200313416A1
公开(公告)日：2020-10-01
申请号：US16365388
申请日：2019-03-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： ELI COLE WARREN , Jerusalem Negash , Kevin A. Ford
IPC: H02G15/013 , F02C7/28 , F01D17/08
Abstract: An egress seal fitting for a bulkhead penetration may comprise a housing, a driver configured to couple to the housing and define a cavity within the housing, and a seal member configured to be disposed within the cavity of the housing, wherein the driver is configured to pass a cable through the housing and apply pressure to the seal member.
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公开(公告)号：US11070041B2
公开(公告)日：2021-07-20
申请号：US16365388
申请日：2019-03-26
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Eli Cole Warren , Jerusalem Negash , Kevin A. Ford
IPC: H02G15/013 , F02C7/28 , F01D17/08
Abstract: An egress seal fitting for a bulkhead penetration may comprise a housing, a driver configured to couple to the housing and define a cavity within the housing, and a seal member configured to be disposed within the cavity of the housing, wherein the driver is configured to pass a cable through the housing and apply pressure to the seal member.
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公开(公告)号：US10808570B2
公开(公告)日：2020-10-20
申请号：US15702190
申请日：2017-09-12
Applicant: United Technologies Corporation
Inventor： Eli Cole Warren , Kevin A. Ford
Abstract: In combination a blade clearance sensor and a radial flow separation wall of a gas turbine engine is provided. The blade clearance sensor is embedded in the radial flow separation wall. The radial flow separation wall comprising: a splitter hoop located radially outward from blades in a first flow path of the gas turbine engine, the splitter hoop being about concentric to a blade path of the blades; and one or more guide vane bases attached to a guide vane located radially outward from the splitter hoop in a second flow path, each of the one or more guide vane bases being securely attached to a radially outward surface of the splitter hoop, wherein the blade clearance sensor is configured to detect a blade clearance between the blades and the splitter hoop.
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公开(公告)号：US20200096331A1
公开(公告)日：2020-03-26
申请号：US16137189
申请日：2018-09-20
Applicant: United Technologies Corporation
Inventor： Eli C. Warren , Kevin A. Ford , Patrick M. Harrington
Abstract: An angled face cap probe includes a housing having a radially inner end and a radially outer end, defining a cavity, and configured to be located radially outward from an airfoil. The angled face cap probe further includes a sensor located in the cavity at the radially inner end of the housing, having a sensor body with a sensing face that is angled to match or substantially match an angle of a radially outward face the airfoil, and having a sensor flat that is elongated in a first direction. The angled face cap probe further includes an outer cap located in the cavity, coupled to the housing, and having an outer cap main body and cap legs that extend radially inward from the outer cap main body to interface with the sensor flat to resist rotation of the sensor relative to the housing.
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