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公开(公告)号：US20220155114A1
公开(公告)日：2022-05-19
申请号：US17589343
申请日：2022-01-31
Applicant: Rosemount Aerospace Inc.
Inventor： Scott Wigen , Greg Allen Seidel , Ram Ranjan , Timothy Thomas Golly , Wayde R. Schmidt , Sameh Dardona , Slade R. Culp
Abstract: An air data probe includes an air data probe body and an additively manufactured heater on the air data probe body.
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公开(公告)号：US11237031B2
公开(公告)日：2022-02-01
申请号：US16545591
申请日：2019-08-20
Applicant: Rosemount Aerospace Inc.
Inventor： Scott Wigen , Greg Allen Seidel , Ram Ranjan , Timothy Thomas Golly , Wayde R. Schmidt , Sameh Dardona , Slade R. Culp
Abstract: An air data probe includes an air data probe body and an additively manufactured heater on the air data probe body, the heater including a first heater layer and a first dielectric layer on the first heater layer. The first dielectric layer makes up an exterior surface of the heater.
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Patent Agency Ranking
公开(公告)号：US20210270144A1
公开(公告)日：2021-09-02
申请号：US16805486
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 an airfoil body, a heater element, and a temperature probe. The airfoil body defines a sensor axis, an insulating cavity, and extends between a leading edge and a trailing edge of the airfoil body. The heater element 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：US10006813B2
公开(公告)日：2018-06-26
申请号：US15588890
申请日：2017-05-08
Applicant: Rosemount Aerospace Inc.
Inventor： Matthew J. T. Gmach , Robert E. Sable , John T. Otto , Scott Wigen
CPC classification number: G01K1/22 , G01K13/00 , G01K13/028
Abstract: A temperature sensor includes a sensor body and a wedge extension. The sensor body extends from a sensor base to an opposed sensor tip along a longitudinal axis. The sensor body has a leading edge and opposed trailing edge. The sensor body also has an interior flow passage with an inlet for fluid communication of fluid into the interior flow passage and an outlet for exhausting fluid out from the interior flow passage. The wedge extension is on the sensor body between the sensor tip and the sensor base on the leading edge of the sensor body.
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公开(公告)号：US09933290B1
公开(公告)日：2018-04-03
申请号：US15624988
申请日：2017-06-16
Applicant: Rosemount Aerospace Inc.
Inventor： Scott Wigen , Walter S. Pekala
CPC classification number: G01F1/44 , B22F3/1055 , B29C67/0051 , B33Y10/00 , B33Y80/00 , F15D1/00 , G01F1/76
Abstract: A flow measurement sensing device includes a first venturi having a first shield portion, an elongated portion connected to an outer surface of the first venturi, and a second venturi housed within the first venturi. The second venturi has a second shield portion and at least one air inlet. The flow measurement sensing device further includes a first integral passageway extending from the air inlet through the elongated portion. The first integral passageway has a first segment with a first cross-sectional shape and a segment with a second cross-sectional shape.
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公开(公告)号：US09624787B2
公开(公告)日：2017-04-18
申请号：US14178351
申请日：2014-02-12
Applicant: Rosemount Aerospace Inc.
Inventor： Scott Wigen
CPC classification number: F01D25/02 , F01D21/003 , G01K13/028
Abstract: A total air temperature sensor includes an airfoil body extending from an airfoil base to an opposed airfoil tip along a longitudinal axis. The airfoil body defines a leading edge and opposed trailing edge. The airfoil body defines an interior flow passage with an inlet for fluid communication of fluid into the interior flow passage and an outlet for exhausting fluid out from the interior flow passage, and wherein the airfoil body defines a bleed passage through the airfoil body between the leading edge and the interior flow passage. A temperature probe is mounted within the interior flow passage for measuring temperature of flow through the interior flow passage to determine total air temperature.
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公开(公告)号：US20150063414A1
公开(公告)日：2015-03-05
申请号：US14189885
申请日：2014-02-25
Applicant: Rosemount Aerospace Inc.
Inventor： Scott Wigen , Matthew J.T. Gmach , Robert E. Sable , John T. Otto
IPC: G01K13/02
CPC classification number: G01K13/028
Abstract: A total air temperature sensor includes a supercritical airfoil body extending from an airfoil base to an opposed airfoil tip along a longitudinal axis. The supercritical airfoil body defines an interior flow passage with an inlet for fluid communication of fluid into the interior flow passage and an outlet for exhausting fluid out from the interior flow passage. A temperature probe is mounted within the interior flow passage for measuring temperature of flow through the interior flow passage to determine total air temperature.
Abstract translation: 总空气温度传感器包括超临界翼型体，其从翼型基部沿着纵向轴线延伸到相对的翼型端头。 超临界翼型体限定了内部流动通道，其具有用于使流体流体连通到内部流动通道中的入口和用于从内部流动通道排出流体的出口。 温度探针安装在内部流动通道内，用于测量通过内部流动通道的流动的温度，以确定总的空气温度。
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