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公开(公告)号：US12209505B2
公开(公告)日：2025-01-28
申请号：US18455193
申请日：2023-08-24
Applicant: Rosemount Aerospace Inc.
Inventor： Andrew Holl , Scott Wigen , Scott D. Isebrand , Robert Edward Sable , Brian Boyd
Abstract: A sensor includes an airfoil body, a heater element, and a temperature probe. The airfoil body defines a sensor axis and having a leading edge, a trailing edge, and an ice accretion feature. The heater element extends axially through the airfoil body between the leading edge and the trailing edge of the airfoil body. The temperature probe extends axially through the airfoil body between the heater element and the trailing edge of the airfoil body. The heater element is axially overlapped by the ice accretion feature to accrete ice chordwise forward of a tip surface aperture. Gas turbine engines, methods of making sensors, and methods of accreting ice on sensors are also described.
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22.发明公开公开(公告)号：US20240209750A1
公开(公告)日：2024-06-27
申请号：US18455193
申请日：2023-08-24
Applicant: Rosemount Aerospace Inc.
Inventor： Andrew Holl , Scott Wigen , Scott D. Isebrand , Robert Edward Sable , Brian Boyd
CPC classification number: F01D21/003 , F01D25/02 , G01K1/08 , G01K1/20 , G01K13/02 , B33Y80/00 , F05D2220/3217 , F05D2220/323
Abstract: A sensor includes an airfoil body, a heater element, and a temperature probe. The airfoil body defines a sensor axis and having a leading edge, a trailing edge, and an ice accretion feature. The heater element extends axially through the airfoil body between the leading edge and the trailing edge of the airfoil body. The temperature probe extends axially through the airfoil body between the heater element and the trailing edge of the airfoil body. The heater element is axially overlapped by the ice accretion feature to accrete ice chordwise forward of a tip surface aperture. Gas turbine engines, methods of making sensors, and methods of accreting ice on sensors are also described.
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23.发明公开公开(公告)号：US20240133317A1
公开(公告)日：2024-04-25
申请号：US18400123
申请日：2023-12-29
Applicant: Rosemount Aerospace Inc.
Inventor： Andrew Holl , Scott Wigen , Robert Edward Sable , Scott D. Isebrand , Brian Boyd
CPC classification number: F01D25/02 , F01D21/12 , G01K13/02 , G01K13/024
Abstract: A sensor includes a mount arranged along a sensor axis, an airfoil body fixed to the mount and having a first face and second face extending along the sensor axis, a heater element, and a temperature probe. The heater element and the temperature probe are positioned within the airfoil body and extend axially along the airfoil body. The airfoil body defines within its interior a pressure channel having an inlet segment extending between the heater element and the first face of the airfoil body to prevent ice formation and/or melt ice entrained within air traversing the pressure channel. Gas turbine engines, methods of removing ice or preventing ice formation, and methods of making sensors are also described.
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公开(公告)号：USD976138S1
公开(公告)日：2023-01-24
申请号：US29758911
申请日：2020-11-19
Applicant: Rosemount Aerospace Inc.
Designer： Scott D. Isebrand
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Patent Agency Ranking
公开(公告)号：US11237183B2
公开(公告)日：2022-02-01
申请号：US16714045
申请日：2019-12-13
Applicant: Rosemount Aerospace Inc.
Inventor： Christopher Sanden , Scott D. Isebrand , Greg Allen Seidel
Abstract: A probe head for an air data probe includes a ceramic body and a heater embedded within the ceramic body.
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26.发明申请公开(公告)号：US20210270149A1
公开(公告)日：2021-09-02
申请号：US16805456
申请日：2020-02-28
Applicant: Rosemount Aerospace Inc.
Inventor： Andrew Holl , Scott Wigen , Robert Edward Sable , Scott D. Isebrand , Brian Boyd
Abstract: A sensor includes a mount arranged along a sensor axis, an airfoil body fixed to the mount and having a first face and second face extending along the sensor axis, a heater element, and a temperature probe. The heater element and the temperature probe are positioned within the airfoil body and extend axially along the airfoil body. The airfoil body defines within its interior a pressure channel having an inlet segment extending between the heater element and the first face of the airfoil body to prevent ice formation and/or melt ice entrained within air traversing the pressure channel. Gas turbine engines, methods of removing ice or preventing ice formation, and methods of making sensors are also described.
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公开(公告)号：US20190383673A1
公开(公告)日：2019-12-19
申请号：US16010011
申请日：2018-06-15
Applicant: Rosemount Aerospace Inc.
Inventor： Scott D. Isebrand
IPC: G01K13/02
Abstract: A total air temperature probe includes a housing including an inlet scoop, an outlet, a main airflow passage extending from the inlet scoop to the outlet, an exit that extends through the housing, and a total air temperature sensor flow passage and a sensor assembly positioned in the total air temperature sensor flow passage. The main airflow passage includes an upper inlet surface extending from the inlet scoop, a lower inlet surface opposite the upper inlet surface and extending from the inlet scoop, an upper outlet surface extending from the upper inlet surface to the outlet, and a lower outlet surface opposite the upper outlet surface and extending from a split point in the housing to the outlet. The total air temperature sensor flow passage branches off from the main airflow passage and extends to the exit. The upper outlet surface is consistently concave toward the outlet.
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公开(公告)号：US20180356293A1
公开(公告)日：2018-12-13
申请号：US15617768
申请日：2017-06-08
Applicant: Rosemount Aerospace Inc.
Inventor： Scott D. Isebrand
CPC classification number: G01K1/08 , G01K13/028 , G01K2013/024
Abstract: A total air temperature probe includes a housing defining a total air temperature sensor flow passage and a sensor assembly positioned within the total air temperature sensor flow passage. The sensor assembly includes an element flow tube, and a sensing element within the element flow tube. An upper portion of the element flow tube is an entrance including a plurality of protrusions that extend in an upstream direction.
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公开(公告)号：US20170338889A1
公开(公告)日：2017-11-23
申请号：US15160422
申请日：2016-05-20
Applicant: Rosemount Aerospace Inc.
Inventor： Nghia T. Dinh , Cuong Tho Huynh , Scott D. Isebrand
Abstract: A sensor assembly comprises a remote data concentrator (RDC) and an optically powered transducer module (OPTM). The RDC transmits a first optical pulse including a parameter request signal along an optical fiber. The OPTM is connected to the optical fiber, and comprises a photodiode, an energy storage device, a sensor, a processor, and a laser. The photodiode receives the first optical pulse, and the energy storage device is charged by the photodiode. The sensor, processor, and laser are powered by discharging the energy storage device. The sensor senses a parameter specified by the parameter request signal. The processor generates a signal packet from the output of the first sensor. The laser transmits a second optical pulse including the signal packet along the optical fiber to the RDC
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