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公开(公告)号：EP3835793A1
公开(公告)日：2021-06-16
申请号：EP20205705.5
申请日：2020-11-04
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： SANDEN, Christopher , ISEBRAND, Scott D. , SEIDEL, Greg
Abstract: A probe head (100) for an air data probe includes a ceramic body (116) and a heater (118) embedded within the ceramic body (116).
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公开(公告)号：EP3872468A1
公开(公告)日：2021-09-01
申请号：EP21159756.2
申请日：2021-02-26
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： HOLL, Andy , WIGEN, Scott , SABLE, Robert E. , ISEBRAND, Scott D. , BOYD, Brian
Abstract: A sensor includes an airfoil body (104), a heater element (134), and a temperature probe (158). The airfoil body (104) defines a sensor axis, an insulating cavity (172), and extends between a leading edge and a trailing edge of the airfoil body. The heater element (134)extends axially within the airfoil body and is positioned between the leading edge and the trailing edge of the airfoil body. The temperature probe extends axially within the airfoil body, is positioned between the heater element and the trailing edge of the airfoil body, and is separated from the heater element by the insulating cavity to limit thermal communication between the temperature probe and the heater element. Gas turbine engines, methods of making sensors, and methods of thermally separating temperature probes and heater elements in sensors are also described.
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公开(公告)号：EP3253068A1
公开(公告)日：2017-12-06
申请号：EP17162983.5
申请日：2017-03-27
Applicant: Rosemount Aerospace Inc.
Inventor： DINH, Nghia T. , HUYNH, Cuong Tho , ISEBRAND, Scott D.
Abstract: A sensor assembly comprises a remote data concentrator (RDC) (14) and an optically powered transducer module (OPTM) (12). The RDC (14) transmits a first optical pulse including a parameter request signal along an optical fiber (16). The OPTM (12) is connected to the optical fiber (16), and comprises a photodiode (22), an energy storage device (30), a sensor (36), a processor (32), and a laser (24). The photodiode (22) receives the first optical pulse, and the energy storage device (30) is charged by the photodiode (22). The sensor (36), processor (32), and laser (24) are powered by discharging the energy storage device (30). The sensor (36) senses a parameter specified by the parameter request signal. The processor (32) generates a signal packet from the output of the first sensor (36). The laser transmits a second optical pulse including the signal packet along the optical fiber to the RDC (14).
Abstract translation: 传感器组件包括远程数据集中器（RDC）（14）和光学驱动的换能器模块（OPTM）（12）。 RDC（14）沿着光纤（16）发送包括参数请求信号的第一光脉冲。 OPTM 12连接到光纤16，并包括光电二极管22，能量存储装置30，传感器36，处理器32和激光器24。 光电二极管（22）接收第一光脉冲，并且能量存储装置（30）由光电二极管（22）充电。 传感器（36），处理器（32）和激光器（24）通过使能量存储装置（30）放电而被供电。 传感器（36）感测由参数请求信号指定的参数。 处理器（32）从第一传感器（36）的输出生成信号包。 激光器将包括信号包的第二光脉冲沿着光纤传输到RDC（14）。
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公开(公告)号：EP3205582A1
公开(公告)日：2017-08-16
申请号：EP17155028.8
申请日：2017-02-07
Applicant: Rosemount Aerospace Inc.
Inventor： ISEBRAND, Scott D.
CPC classification number: G01K13/028 , B64D43/00 , B64D45/00
Abstract: A total air temperature probe (10) includes a housing (12) having inner surfaces defining an airflow passage, a first section of the airflow passage of the housing (12) having an airflow inlet scoop with a first cross-sectional area and an inertial separation bend downstream of the airflow inlet scoop, wherein the airflow passage is configured to be substantially straight; and a second section of the airflow passage of the housing having a main exit channel and an elongated outlet with a second cross-sectional area, wherein the airflow passage is contoured to direct particle deflections to the elongated outlet, wherein the second section is downstream from the first section, and wherein the first cross-sectional area is greater than the second cross-sectional area.
Abstract translation: 总空气温度探测器（10）包括具有限定气流通道的内表面的壳体（12），壳体（12）的气流通道的第一部分具有带有第一横截面面积的气流入口勺和惯性 在所述气流入口勺下游的分离弯曲部，其中所述气流通道构造成基本笔直; 并且所述壳体的所述气流通道的第二部分具有主出口通道和具有第二横截面区域的细长出口，其中所述气流通道构造成将颗粒偏转引导至所述细长出口，其中所述第二部分位于所述细长出口的下游 第一部分，并且其中第一横截面积大于第二横截面积。
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公开(公告)号：EP3462154A1
公开(公告)日：2019-04-03
申请号：EP18196242.4
申请日：2018-09-24
Applicant: Rosemount Aerospace Inc.
Inventor： GILB, Andrew , ISEBRAND, Scott D.
IPC: G01K13/02
Abstract: A probe (10) includes a housing (14) defining a flow passage (24) for a first fluid and having an entrance port (20) and an exit port (30), a sensor configured to sense a parameter of the first fluid and positioned within the flow passage (24), and a hoop ejector (12) connected externally to the housing (14) such that a channel (54) of the hoop ejector (12) surrounds the exit port (30). The hoop ejector (12) has a plurality of holes (58) configured to port a second fluid from the channel (54) such that the first fluid is aspirated from the flow passage (24) and out through the exit port (30).
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Patent Agency Ranking
公开(公告)号：EP3413025A1
公开(公告)日：2018-12-12
申请号：EP18175038.1
申请日：2018-05-30
Applicant: Rosemount Aerospace Inc.
Inventor： ISEBRAND, Scott D.
IPC: G01K13/02
CPC classification number: G01K1/08 , G01K13/028 , G01K2013/024
Abstract: A total air temperature probe (10) includes a housing (14) defining a total air temperature sensor flow passage (28) and a sensor assembly (18) positioned within the total air temperature sensor flow passage (28). The sensor assembly (18) includes an element flow tube (12), and a sensing element (32) within the element flow tube (12). An upper portion of the element flow tube (12) is an entrance (40) including a plurality of protrusions (42) that extend in an upstream direction.
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公开(公告)号：EP4160222A1
公开(公告)日：2023-04-05
申请号：EP22198127.7
申请日：2022-09-27
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： ISEBRAND, Scott D. , SEIDEL, Greg
Abstract: A probe head of an air data probe includes a unitary body (22) extending from a first end (18) to a second end (20) of the probe head and a rod heater. The body includes an inlet (28) adjacent the first end of the probe head, an air passageway (30) extending through the body from the inlet to the second end of the probe head, a water dam (32) extending radially through the body such that the air passageway is redirected around the water dam, and a heater bore (34) extending within the body. The rod heater (24) is positioned within the heater bore.
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8.发明公开
公开(公告)号：EP3872471A1
公开(公告)日：2021-09-01
申请号：EP21158728.2
申请日：2021-02-23
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： HOLL, Andrew , WIGEN, Scott , SABLE, Robert E. , ISEBRAND, Scott D. , BOYD, Brian
Abstract: A sensor (100) includes a mount (102) arranged along a sensor axis (114), an airfoil body (104) fixed to the mount (102) and having a first face (120) and second face (122) extending along the sensor axis (114), a heater element (134), and a temperature probe (158). The heater element (134) and the temperature probe (158) are positioned within the airfoil body (104) and extend axially along the airfoil body (104). The airfoil body defines within its interior a pressure channel (130) having an inlet segment (152) extending between the heater element (134) and the first face (120) of the airfoil body (104) to prevent ice formation and/or melt ice entrained within air traversing the pressure channel (130). Gas turbine engines, methods of removing ice or preventing ice formation, and methods of making sensors are also described.
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9.发明公开
公开(公告)号：EP3872467A1
公开(公告)日：2021-09-01
申请号：EP21157712.7
申请日：2021-02-17
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： HOLL, Andrew , WIGEN, Scott , ISEBRAND, Scott D. , SABLE, Robert E. , BOYD, Brian
Abstract: A sensor (100) includes an airfoil body (104), a heater element (134), and a temperature probe (158). The airfoil body (104) defines a sensor axis (114) and having a leading edge (116), a trailing edge (118), and an ice accretion feature (195). The heater element (134) extends axially through the airfoil body (104) between the leading edge (116) and the trailing edge (118) of the airfoil body (104). The temperature probe (158) extends axially through the airfoil body (104) between the heater element (134) and the trailing edge (118) of the airfoil body (104). The heater element (134) is axially overlapped by the ice accretion feature (195) to accrete ice chordwise forward of a tip surface aperture (170). Gas turbine engines, methods of making sensors, and methods of accreting ice on sensors are also described.
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公开(公告)号：EP3581901A1
公开(公告)日：2019-12-18
申请号：EP19180681.9
申请日：2019-06-17
Applicant: ROSEMOUNT AEROSPACE INC.
Inventor： ISEBRAND, Scott D.
IPC: G01K13/02
Abstract: A total air temperature probe includes a housing (12) including an inlet scoop (18), an outlet (20), a main airflow passage (22) extending from the inlet scoop (18) to the outlet (20), an exit that extends through the housing (12), 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 (22) includes an upper inlet surface (44) extending from the inlet scoop (18), a lower inlet surface (46) opposite the upper inlet surface (44) and extending from the inlet scoop (18), an upper outlet surface (48) extending from the upper inlet surface (44) to the outlet (20), and a lower outlet surface (50) opposite the upper outlet surface (48) and extending from a split point (27) in the housing (12) to the outlet (20). The total air temperature sensor flow passage branches off from the main airflow passage (22) and extends to the exit. The upper outlet surface (48) is consistently concave toward the outlet (20).
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