• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    A heating system for a dynamic air turbine includes a heated strainer which is disposed on an air inlet defined by a strut. The strut has a first end which is connected to a generator which is operatively connected to a turbine which is connected to a second end of the strut. The heated strainer has a heating element housed inside.
    公开号:FR3054528A1
    申请号:FR1757130
    申请日:2017-07-27
    公开日:2018-02-02
    发明作者:Scott J. Marks
    申请人:Hamilton Sundstrand Corp；
    IPC主号:
    专利说明:

    © Publication no .: 3,054,528 (to be used only for reproduction orders)
    ©) National registration number: 17 57130 ® FRENCH REPUBLIC
    NATIONAL INSTITUTE OF INDUSTRIAL PROPERTY
    COURBEVOIE © Int Cl 8 : B 64 D 41/00 (2017.01), F 02 C 7/047
    A1 PATENT APPLICATION
    ©) Date of filing: 07.27.17. © Applicant (s): HAMILTON SUNDSTRAND CORPO- © Priority: 07.29.16 US 15223426. RATION— US. @ Inventor (s): MARKS SCOTT J .. ©) Date of public availability of the request: 02.02.18 Bulletin 18/05. ©) List of documents cited in the report preliminary research: The latter was not established on the date of publication of the request. (© References to other national documents ® Holder (s): HAMILTON SUNDSTRAND CORPORA- related: TION. ©) Extension request (s): © Agent (s): CABINET PLASSERAUD.
    DYNAMIC AIR TURBINE COOLING AIR INLET STRAINER HEATING SYSTEM.
    tbp A heating system for a dynamic air turbine includes a heated strainer which is arranged on an air inlet defined by a strut. The strut has a first end which is connected to a generator which is operatively connected to a turbine which is connected to a second end of the strut. The heated strainer has a heating element housed inside.
    FR 3 054 528 - A1

    i
    AIR INTAKE STRAINER HEATING SYSTEM
    DYNAMIC AIR TURBINE COOLING
    Background
    Aircraft have a dynamic air turbine system that is configured to supply electrical or hydraulic power to the aircraft in certain situations. The dynamic air turbine system is stored inside the aircraft and is selectively deployed in an air flow. The dynamic air turbine system can receive cooling air to cool the electrical equipment of the dynamic air turbine system. The cooling air inlet has an inlet strainer to prevent foreign objects from entering the generator.
    brief description
    One embodiment of the present disclosure provides a dynamic air turbine system. The dynamic air turbine system includes a strut, a heated strainer, a turbine and a generator. The strut is pivotally connected to a mounting frame which is operatively connected to an aircraft structure. The strut is defined by a strut body which extends between a first end and a second end. The body of the strut defines an air intake. The heated strainer has a heating element which is housed inside the heated strainer. The turbine is arranged at the second end of the strut. The generator is located near the first end of the strut. The generator is connected by drive to the turbine via a drive shaft.
    In addition to the characteristic or characteristics described here, the heating element is electrically connected to the generator.
    In addition to the characteristic or characteristics described here, the heating element is electrically isolated from a power source of the aircraft.
    In addition to the feature (s) described here, the air inlet is configured as a cooling air inlet which supplies cooling air to the generator.
    In addition to the characteristic or characteristics described here, the generator defines a cooling air outlet which evacuates the cooling air which is supplied to the generator.
    Another embodiment of the present disclosure provides a dynamic air turbine system. The dynamic air turbine system includes a strut and a heating system. The strut has a first end which is connected to a generator which is connected by drive to a turbine which is connected to a second end. The strut has an air inlet which is arranged near the first end. The heating system is electrically connected to the generator. The heating system has a heated strainer which is arranged on the air inlet.
    In addition to the feature (s) described herein, the heated strainer includes a heating element disposed between a first strainer element and a second strainer element which is spaced from and disposed opposite the first strainer element.
    In addition to the feature (s) described herein, the heated strainer includes a film heating element applied to at least one of a first strainer element and a second strainer element which is spaced from the first strainer element and disposed opposite of it.
    In addition to the characteristic or characteristics described here, the generator defines an air outlet.
    In addition to the feature (s) described here, the air inlet includes a first inlet window disposed adjacent to a second inlet window.
    In addition to the characteristic or characteristics described here, the first entrance window is separated from the second entrance window by a first partition.
    In addition to the characteristic or characteristics described here, the air intake further comprises a third intake window disposed adjacent to the second intake window.
    In addition to the characteristic or characteristics described here, the second entrance window is separated from the third entrance window by a third partition.
    Yet another embodiment of the present disclosure provides a heating system for a dynamic air turbine. The heating system includes a heated strainer which is arranged on an air inlet defined by a strut. The strut has a first end which is connected to a generator which is operatively connected to a turbine which is connected to a second end of the strut. The heated strainer has a heating element housed inside.
    In addition to the characteristic or characteristics described here, the heating element is electrically connected to the generator.
    In addition to the characteristic or characteristics described here, in response to the rotation of the turbine, the generator supplies energy to the heating element.
    Brief description of the drawings
    The subject matter which is considered to be this disclosure is specifically emphasized and claimed separately in the feature claims and feature benefits at the end of the specification. The precedents and others of this disclosure appear clearly on reading the following detailed description made in conjunction with the accompanying drawings in which:
    Figure 1 is a perspective view of a dynamic air turbine system having a heating system in a deployed position;
    Figure 2 is a partial perspective view of a strut having an air inlet of the dynamic air turbine system; and Figure 3 is a diagram of a heating system provided with the dynamic air turbine system.
    detailed description
    If we now consider the figures, in which the invention will be described with reference to specific embodiments, without being limited thereto, it should be understood that the embodiments disclosed are purely illustrative of the invention which can be implemented in various and alternative forms. The figures are not necessarily to scale; certain characteristics can be accentuated or attenuated to show details of particular components. Therefore, the specific structural and functional details disclosed herein are not to be construed as limiting, but merely as a representative basis for teaching those skilled in the art to use the present invention in various ways.
    Referring to FIG. 1, a dynamic air turbine system 10 is shown. The dynamic air turbine system 10 is fixed to an aircraft structure. The dynamic air turbine system 10 can be disposed in a mobile or pivoting manner inside the fuselage of the aircraft, of a wing-fuselage junction fairing, of a portion of the aircraft front cone, or in other positions. The dynamic air turbine system 10 is movable between a stored position and a deployed position.
    The dynamic air turbine system 10 includes a mounting frame 20, a strut 22, a generator 24, a turbine 26, and a heating system 28. The mounting frame 20 is operatively connected to the structure of the aircraft. The mounting frame 20 is operatively connected to an actuator arranged to move the strut 22 between the stored position and the deployed position.
    The strut 22 is connected to the generator 24 which is pivotally connected to the mounting frame 20 or directly connected to the aircraft structure. The strut 22 includes a strut body 40 which extends between a first end 42 and a second end 44. The strut body 40 is configured as a hollow body which extends along an axis. The strut body 40 defines an air inlet 50. The air inlet 50 is disposed between the first end 42 and the second end 44 of the strut 22. The air inlet 50 is disposed closer to the first end 42 than the second end 44 of the strut 22.
    The air inlet 50 extends from an outer surface of the strut body 40 through an inner surface of the strut body 40. The air inlet 50 includes a single inlet window or multiple windows of The inlet, for illustrative purposes, an air inlet with multiple windows is shown. The air inlet 50 includes a first inlet window 52, a second inlet window 54 which is disposed adjacent to the first inlet window 52, and a third inlet window 56 which is arranged adjacent to the second entry window 54. Each entry window is configured in the form of an elongated window whose length is greater than its width. In at least one embodiment, a frame 58 is arranged around the air inlet 50 and surrounds the first inlet window 52, the second inlet window 54 and the third inlet window 56. The frame 58 extends above the exterior surface of the strut body 40.
    The first entry window 52 is separated from the second entry window 54 by a first partition 60. Each of the first entry window 52 and the second entry window 54 have a width which is greater than a width of the first partition 60.
    The second entry window 54 is separated from the third entry window 56 by a second partition 62. Each of the second entry window 54 and the third entry window 56 have a width which is greater than a width of the second partition 62.
    The generator 24 is operationally connected to the first end 42 of the strut 22. The generator 24 is pivotally connected to the mounting frame 20 or to the structure of the aircraft through the generator 24. The generator 24 defines an input of generator cooling air and a generator cooling air outlet 70. The dynamic air or cooling air which is supplied through the air inlet 50 defined by the strut body 40 of the strut 22 flows through the hollow body of the body 40 towards the cooling air inlet generator strut, through the generator 24, and out of the cooling air outlet of the generator 70. As such, the air inlet 50 is configured as a cooling air inlet which supplies cooling air to electronic components of the generator 24.
    The generator 24 is configured to include a permanent magnet generator.
    The turbine 26 is disposed at the second end 44 of the strut 22. The turbine 26 includes a gearbox 80, a turbine hub 82 and blades 84. The turbine hub 82 is operatively connected to the gearbox 80. The blades 84 extend from the turbine hub 82. The blades 84 and the turbine hub 82 are arranged to rotate in response to the encounter of dynamic air and the blades 84 while the turbine system dynamic air 10 is in the deployed position. The turbine 26 is connected by drive or operationally connected to the generator 24 by a drive shaft which extends between the generator 24 and the gearbox 80. The gearbox 80 is configured to communicate the rotary movement of the turbine hub 82 and vanes 84 in the form of the rotary movement of the drive shaft for actuating the generator 24.
    Rotation of the turbine 26 rotates the drive shaft which rotates the generator 24 and supplies power to a generator control unit 72 and to the heating system 28. The generator 24 is configured to start providing electrical energy to the heating system 28 as soon as the turbine 26 starts to rotate.
    Refer to Figures 1 to 3 in which the heating system 28 is configured to inhibit the formation of ice on the air inlet 50 defined by the strut body 40 of the strut 22 while the air turbine system dynamic 10 is deployed and operational. The operation of the generator 24 supplies energy to the heating system 28 which is independent of or isolated from a power system or a power source of the aircraft. The heating system 28 includes a heated strainer 90 having a heating element 92 which is electrically connected to the generator 24.
    The heated strainer 90 defines a plurality of orifices which facilitate or allow air flow through the heated strainer 90 and into the air inlet 50. The heated strainer 90 having a heating element 92 is disposed on or above above the air inlet 50 and is fixed to the strut body 40 of the strut 22. In at least one embodiment, the heated strainer 90 comprising a heating element 92 is operatively connected to the frame 58 which extends around from the air inlet 50. The heating element 92 is electrically connected to the generator 24 and is electrically isolated from a power source of the aircraft. The heating element 92 is placed inside the heated strainer 90.
    The heated strainer 90 includes a first strainer element 100 and a second strainer element 102. The first strainer element 100 is spaced from the second strainer element 102 so that the heating element 92 is disposed between the first strainer element 100 and the second strainer element 102. In at least one embodiment, the heating element 92 is sandwiched between the first strainer element 100 and the second strainer element 102. In at least one embodiment, the the heating element 92 is a film heating element which is applied to at least one of the first strainer element 100 and the second strainer element 102. In at least one embodiment, the heating element 92 is woven with or integrated with at least one of the first strainer element 100 and the second strainer element 102. In such an embodiment, the heating element 92 includes a plurality of electroconductive / electroconductive elements or fibers. In at least one embodiment, at least one of the first strainer element 100 and the second strainer element 102 of the heated strainer 90 is impregnated with the heating element 92.
    In at least one embodiment, the heating element 92 is a resistant heating element, a surface-type heating element, a sheet-type heating element, a channel-shaped heating structure or the like which produces or generates heat in response to the supply of electricity by the generator 24 to the heating element 92. The heating element 92 extends between electrical connectors or electrodes 106 which are electrically connected to the generator 24 by means of wiring which is routed from the inside through the strut body 40 from the strut 22 to the generator 24. The electrodes 106 are positioned inside or extend from opposite ends of the heated strainer 90. The electrodes 106 are housed or molded into a portion of at least one of the first strainer element 100 and the second strainer element 102.
    Although the present disclosure has been described in detail in connection with only a limited number of embodiments, it will readily be understood that the present disclosure is not limited to the said disclosed embodiments. On the contrary, this disclosure may be modified to incorporate any number of variants, modifications, replacements or equivalent arrangements not described so far, but which take into account the scope of this disclosure. In addition, although various embodiments of the present disclosure have been described, it should be understood that aspects of the present disclosure may include only some of the embodiments described. Accordingly, the present disclosure is not to be construed as limited by the foregoing description, but is limited only by the scope of the appended claims.
    ίο
    权利要求:
    Claims (11)
    [1" id="c-fr-0001]
    1. Dynamic air turbine system, comprising:
    a strut having a first end which is connected to a generator which is drively connected to a turbine connected to a second end, the strut being provided with an air inlet which is disposed near the first end; and a heating system being electrically connected to the generator, the heating system having a heated strainer disposed on the air inlet.
    [2" id="c-fr-0002]
    2. A dynamic air turbine system according to claim 1, wherein the heated strainer includes a heating element disposed between a first strainer element and a second strainer element which is spaced from the first strainer element and disposed opposite this one.
    [3" id="c-fr-0003]
    The dynamic air turbine system of claim 1, wherein the heated strainer includes a film heater applied to at least one of a first strainer element and a second strainer element which is spaced apart. of the first strainer element and disposed opposite it.
    [4" id="c-fr-0004]
    4. Dynamic air turbine system according to claim 1, wherein the generator defines an air outlet.
    [5" id="c-fr-0005]
    5. The dynamic air turbine system of claim 1, wherein the air inlet includes a first inlet window disposed adjacent to a second inlet window.
    [6" id="c-fr-0006]
    6. Dynamic air turbine system according to claim 5, in which the first entry window is separated from the second entry window by a first partition.
    [7" id="c-fr-0007]
    7. A dynamic air turbine system according to claim 6, wherein the air inlet further includes a third inlet window disposed adjacent to the second inlet window.
    [8" id="c-fr-0008]
    8. Dynamic air turbine system according to claim 7, wherein the second entrance window is separated from the third entrance window by a third partition.
    [9" id="c-fr-0009]
    9. Heating system for a dynamic air turbine, comprising:
    a heated strainer disposed on an air inlet defined by a strut having a first end connected to the generator which is operatively connected to a turbine connected to a second end, the heated strainer having a heating element housed therein.
    [10" id="c-fr-0010]
    10. The heating system according to claim 9, wherein the heating element is electrically connected to the generator.
    [11" id="c-fr-0011]
    11. A heating system according to claim 10, wherein in response to the rotation of the turbine, the generator supplies energy to the heating element.
    1/2
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    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US5484120A|1994-03-11|1996-01-16|Sundstrand Corporation|Support strut for ram air driven turbine|
    US6127758A|1997-09-17|2000-10-03|Alliedsignal Inc.|Ram air turbine system|
    US6503056B2|2001-04-24|2003-01-07|Honeywell International Inc.|Heating device and method for deployable ram air turbine|
    US8648481B2|2006-06-10|2014-02-11|Star Sailor Energy, Inc.|Wind generator with energy enhancer element for providing energy at no wind and low wind conditions|
    FR2914016B1|2007-03-19|2009-07-03|Turbomeca Sa|DEVICE FOR DEFROSTING AN AIR INTAKE OF A GAS TURBINE|
    US8641379B2|2010-03-24|2014-02-04|Hamilton Sundstrand Corporation|Hybrid ram air turbine|
    WO2013033654A1|2011-08-31|2013-03-07|De Rochemont L Pierre|Fully integrated thermoelectric devices and their application to aerospace de-icing systems|
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    US10099772B2|2014-10-31|2018-10-16|Hamilton Sundstrand Corporation|Ice-shedding spinner for ram air turbine|
    US9642190B2|2015-05-29|2017-05-02|Philip Jarvinen|Embedded turbofan deicer system|
    US10273881B2|2016-04-06|2019-04-30|General Electric Company|Foreign object damage screen for gas turbine system|
    US10077118B2|2016-06-06|2018-09-18|Hamilton Sundstrand Corporation|Integral rat generator cooling holes|US10077118B2|2016-06-06|2018-09-18|Hamilton Sundstrand Corporation|Integral rat generator cooling holes|
    US10322815B1|2018-03-22|2019-06-18|Hamilton Sundstrand Corporation|Stored electrical energy assisted ram air turbinesystem|
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    法律状态:
    2018-06-20| PLFP| Fee payment|Year of fee payment: 2 |
    2019-03-01| PLSC| Publication of the preliminary search report|Effective date: 20190301 |
    2019-06-21| PLFP| Fee payment|Year of fee payment: 3 |
    2020-06-23| PLFP| Fee payment|Year of fee payment: 4 |
    2021-06-23| PLFP| Fee payment|Year of fee payment: 5 |
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    US15/223,426|US10207814B2|2016-07-29|2016-07-29|Ram air turbine cooling inlet screen heating system|
    US15223426|2016-07-29|
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