WO1990008695A1 - Bloc porte-balai retractable - Google Patents

Bloc porte-balai retractable Download PDF

Info

Publication number
WO1990008695A1
WO1990008695A1 PCT/US1989/000449 US8900449W WO9008695A1 WO 1990008695 A1 WO1990008695 A1 WO 1990008695A1 US 8900449 W US8900449 W US 8900449W WO 9008695 A1 WO9008695 A1 WO 9008695A1
Authority
WO
WIPO (PCT)
Prior art keywords
brush
carrier
annular surface
withdrawing
rotating
Prior art date
Application number
PCT/US1989/000449
Other languages
English (en)
Inventor
Jon H. Young
Original Assignee
United Technologies Corporation
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corporation filed Critical United Technologies Corporation
Priority to PCT/US1989/000449 priority Critical patent/WO1990008695A1/fr
Publication of WO1990008695A1 publication Critical patent/WO1990008695A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R39/00—Rotary current collectors, distributors or interrupters
    • H01R39/02—Details for dynamo electric machines
    • H01R39/42—Devices for lifting brushes

Definitions

  • the present invention relates to a device for transferring electrical power between a stationary frame and a rotating component, such as a propeller.
  • Propeller driven aircraft require, on occasion, the application of heat to the surfaces of the propeller blades and spinner for removing or preventing the formation of ice.
  • One such method of ice removal is by means of electrically heated elements on or beneath the surfaces and powered as required by a source of electrical energy carried on the main body of the aircraft.
  • the electric power is transferred to the rotating propeller assembly by means of a brush block or carrier holding one or more conductive carbon brushes which are resiliently urged against corresponding conductive rings disposed in the rotating propeller assembly and concentrically about the propeller shaft.
  • the present invention provides a retractable brush block which establishes electrical contact with a rotating component only during periods wherein the transfer of electric power across the rotating gap is required.
  • the brush block according to the present invention is mounted on a movable support which is selectively driven out of contact with the rotating component by a solenoid or other actuator.
  • a biasing means is provided for continually urging the brush block toward one or more annular conductive surfaces on the rotating component for the purpose of achieving a fail-safe condition in the event of a failure of the withdrawing actuator.
  • Figure 1 shows a view of a brush block according to the present invention installed in a propeller driven aircraft.
  • Figure 2 shows a cross section of one embodiment of the present invention.
  • FIG. 1 shows a brush block energy transfer arrangement 10 according to the present invention as installed in an aircraft 12 having a propeller assembly 14 driven by a shaft 16 rotating about an axis 18.
  • the brush block 20 is disposed adjacent the propeller assembly 14, and more specifically adjacent the rear bulkhead 22 of the assembly 14. Included in the rear bulkhead 22 are one or more annular conductive copper surfaces 24 which contact, at least during periods wherein it is desired to transfer electrical power to the propeller assembly 14, corresponding carbon brushes 26 carried by the brush block 20.
  • the brush block 20 according to the present invention is shown in Figure 1 as being pivotally mounted 28 to the nonrotating portion 30 of the aircraft 12.
  • the brush block 20 is pivoted about the pivot point 28 by means of a linear or other actuator 32 which selectively positions the brush block 20 as required.
  • the actuator 32 positions the brush block 20 proximate the rotating bulkhead 22 such that the brushes 26 contact the corresponding conductive rings 24. Direct electrical contact between the rotating propeller assembly 14 and the nonrotating portion 30 of the aircraft 12 is thus established.
  • a relay (not shown) or other power interrupting device may optionally be provided for ensuring that the brushes and conductive rings do not "arc over" as the brush block is reciprocated between the operating and retracted positions.
  • retractable brush block arrangement 10 is equally effective in circumstances or arrangements wherein there is a need for only one conductive ring 24 and corresponding brush 26.
  • the use of multiple rings 24 and brushes 26 follows typical practice of utilizing a plurality of blade surface heating circuits (not shown) for sequentially deicing individual or opposing pairs of propeller blades 36.
  • actuator 32 is selectively operated to retract the brush block 20 away from the bulkhead 22 and conductive rings 24, thereby separating the brushes 26 and rings 24 and eliminating frictional wear therebetween.
  • FIG. 2 shows a more detailed cross section of another embodiment 38 of the retractable brush block according to the present invention.
  • the brush block 38 includes a carrier 40 supported by a sliding mount 42 which is in turn secured to the nonrotating airframe 30.
  • Individual brushes 26 are disposed in the carrier 40 and selectively positioned so as to contact corresponding annular conductive rings 24 disposed concentrically about the axis of rotation 18 (not shown in Figure 2) in the bulkhead 22.
  • An actuator 44 is provided for selectively withdrawing the carrier 40 axially away from the bulkhead 22 thereby separating the brushes 26 and surfaces 24.
  • biasing means 46 in the form of coil springs or the like for continually urging the carrier 40 axially toward the conductive surfaces 24.
  • the actuator 44 preferably an electrically operated solenoid, is of sufficient size to overcome the spring force 46 when energized, thus withdrawing the carrier 40 and separating the surfaces 24 and brushes 26.
  • solenoid actuator 44 is deenergized and the biasing means 46 operates to drive the carrier 40 axially toward the surfaces 24 establishing contact with the brushes 34.
  • the carrier 40 may be retained within the sliding mount 42 by any of a variety of methods or structures, such as the interfering shoulders 48, 50 shown in Figure 2. Electrical power is transferred between the nonrotating structure 30 and the carrier 40 by flexible wiring 52, etc.
  • retractable connector is well suited for any of a variety of applications wherein it is desired to establish intermittent direct electrical contact between two members across a rotating gap.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Motor Or Generator Current Collectors (AREA)

Abstract

Dans le porte-balai rétractable décrit, l'énergie électrique est transférée à un élément rotatif (14) par un anneau conducteur rotatif (24) et par un porte-balai rétractable (20). Au moins un balai (26) du porte-balai (20) entre en contact avec l'anneau conducteur (24), lors du transfert d'énergie électrique. Lorsque le porte-balai (20) est en position rétractée, le balai (26) et l'anneau conducteur (24) sont séparés.
PCT/US1989/000449 1989-02-06 1989-02-06 Bloc porte-balai retractable WO1990008695A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/US1989/000449 WO1990008695A1 (fr) 1989-02-06 1989-02-06 Bloc porte-balai retractable

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/US1989/000449 WO1990008695A1 (fr) 1989-02-06 1989-02-06 Bloc porte-balai retractable

Publications (1)

Publication Number Publication Date
WO1990008695A1 true WO1990008695A1 (fr) 1990-08-09

Family

ID=22214817

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US1989/000449 WO1990008695A1 (fr) 1989-02-06 1989-02-06 Bloc porte-balai retractable

Country Status (1)

Country Link
WO (1) WO1990008695A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2508719A (en) * 2012-10-26 2014-06-11 Hamilton Sundstrand Corp Retractable contact assembly
EP2860111A1 (fr) * 2013-10-14 2015-04-15 Hamilton Sundstrand Corporation Conception de brosse pour système de dégivrage d'hélice
CN106737368A (zh) * 2016-12-13 2017-05-31 惠阳航空螺旋桨有限责任公司 一种调整导电环与径向刷架组件位置的工具
CN114275634A (zh) * 2021-12-14 2022-04-05 广东电网有限责任公司 一种自动测试线收卷装置
CN114934925A (zh) * 2022-06-09 2022-08-23 无锡市美泰克精密机械有限公司 一种高可靠性电液滑环阀块

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1124360B (de) * 1959-09-25 1962-02-22 English Electric Co Ltd Elektrischer Stellmotor fuer das Getriebe von hydraulischen Pumpen, Turbinen oder umschaltbaren Pumpen-Turbinen mit Stromzufuehrung ueber Schleifringe und Buersten
FR1340953A (fr) * 1962-09-13 1963-10-25 Materiel Electrique S W Le Dispositif de relevage de balais frottant sur des bagues collectrices
US4386749A (en) * 1977-03-04 1983-06-07 The B. F. Goodrich Company Propeller deicer
GB2158524A (en) * 1984-05-11 1985-11-13 United Technologies Corp Heater burnout protection for aircraft propeller deicing system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1124360B (de) * 1959-09-25 1962-02-22 English Electric Co Ltd Elektrischer Stellmotor fuer das Getriebe von hydraulischen Pumpen, Turbinen oder umschaltbaren Pumpen-Turbinen mit Stromzufuehrung ueber Schleifringe und Buersten
FR1340953A (fr) * 1962-09-13 1963-10-25 Materiel Electrique S W Le Dispositif de relevage de balais frottant sur des bagues collectrices
US4386749A (en) * 1977-03-04 1983-06-07 The B. F. Goodrich Company Propeller deicer
US4386749B1 (en) * 1977-03-04 1995-09-12 Goodrich Co B F Propeller deicer
GB2158524A (en) * 1984-05-11 1985-11-13 United Technologies Corp Heater burnout protection for aircraft propeller deicing system

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2508719A (en) * 2012-10-26 2014-06-11 Hamilton Sundstrand Corp Retractable contact assembly
US8894418B2 (en) 2012-10-26 2014-11-25 Hamilton Sundstrand Corporation Retractable contact assembly
GB2508719B (en) * 2012-10-26 2016-01-06 Hamilton Sundstrand Corp Retractable contact assembly
EP2860111A1 (fr) * 2013-10-14 2015-04-15 Hamilton Sundstrand Corporation Conception de brosse pour système de dégivrage d'hélice
US9970300B2 (en) 2013-10-14 2018-05-15 Hamilton Sundstrand Corporation Brush design for propeller deicing system
CN106737368A (zh) * 2016-12-13 2017-05-31 惠阳航空螺旋桨有限责任公司 一种调整导电环与径向刷架组件位置的工具
CN114275634A (zh) * 2021-12-14 2022-04-05 广东电网有限责任公司 一种自动测试线收卷装置
CN114275634B (zh) * 2021-12-14 2024-01-23 广东电网有限责任公司 一种自动测试线收卷装置
CN114934925A (zh) * 2022-06-09 2022-08-23 无锡市美泰克精密机械有限公司 一种高可靠性电液滑环阀块
CN114934925B (zh) * 2022-06-09 2023-08-18 无锡市美泰克精密机械有限公司 一种高可靠性电液滑环阀块

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