CA2609923A1 - Variable speed transmission for a rotary wing aircraft - Google Patents

Variable speed transmission for a rotary wing aircraft Download PDF

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Publication number
CA2609923A1
CA2609923A1 CA002609923A CA2609923A CA2609923A1 CA 2609923 A1 CA2609923 A1 CA 2609923A1 CA 002609923 A CA002609923 A CA 002609923A CA 2609923 A CA2609923 A CA 2609923A CA 2609923 A1 CA2609923 A1 CA 2609923A1
Authority
CA
Canada
Prior art keywords
gearbox
clutch
speed
freewheel
recited
Prior art date
Legal status (The legal status 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 status listed.)
Granted
Application number
CA002609923A
Other languages
French (fr)
Other versions
CA2609923C (en
Inventor
Peter X. Palcic
Todd Garcia
Yuriy Z. Gmirya
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sikorsky Aircraft Corp
Original Assignee
Sikorsky Aircraft Corporation
Peter X. Palcic
Todd Garcia
Yuriy Z. Gmirya
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 Sikorsky Aircraft Corporation, Peter X. Palcic, Todd Garcia, Yuriy Z. Gmirya filed Critical Sikorsky Aircraft Corporation
Publication of CA2609923A1 publication Critical patent/CA2609923A1/en
Application granted granted Critical
Publication of CA2609923C publication Critical patent/CA2609923C/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B64C27/10—Helicopters with two or more rotors arranged coaxially
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
    • B64C2027/8236—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft including pusher propellers
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T74/00—Machine element or mechanism
    • Y10T74/19—Gearing
    • Y10T74/19023—Plural power paths to and/or from gearing
    • Y10T74/19051—Single driven plural drives

Abstract

A transmission gearbox for a rotary-wing aircraft includes a main gearbox and a variable speed gearbox in meshing engagement with the main rotor gearbox.
The variable speed gearbox permits at least two different RPMs for the main rotor system without disengaging the engine(s) or changing engine RPMs. The variable speed gearbox includes a clutch, preferably a multi-plate clutch, and a freewheel unit for each engine. A gear path drives the main gearbox in a "high rotor speed mode" when the clutch is engaged to drive the main rotor system at high rotor rpm for hover flight profile. A reduced gear path drives the main gearbox in a "low rotor speed mode" when the clutch is disengaged and power is transferred through the freewheel unit, to drive the main rotor system at lower rotor rpm for high speed flight. The variable speed gearbox may be configured for a tail drive system that operates at a continuous speed, a tail drive system that changes speed with the main rotor shaft or for no tail drive system.

Claims (22)

1. A transmission gearbox for a rotary-wing aircraft comprising:
a main gearbox; and a variable speed gearbox in meshing engagement with said main gearbox, said variable speed gearbox including a gear path having a clutch and a reduced gear path having a freewheel unit, said main gearbox driven at a first speed in response to engagement of said clutch, said main gearbox driven at a second speed less than said first speed in response to disengagement of said clutch.
2. The transmission gearbox as recited in claim 1, wherein said main gearbox driven is at a first speed in response to engagement of said clutch such that a freewheel output of said freewheel unit overruns a freewheel input of said freewheel unit.
3. The transmission gearbox as recited in claim 1, wherein said main gearbox driven at a second speed less than said first speed in response to disengagement of said clutch such that a clutch output of said clutch rotates at a speed less than a clutch input of said clutch, said freewheel output driven by said freewheel input.
4. The transmission gearbox as recited in claim 1, wherein an output of said gear path downstream of said clutch and an output of said reduced gear path downstream of said freewheel unit are driven in both said first speed and said second speed.
5. The transmission gearbox as recited in claim 1, further comprising a rotor system driven by said main gearbox.
6. The transmission gearbox as recited in claim 5, wherein said rotor system includes a coaxial counter-rotating rotor system.
7. The transmission gearbox as recited in claim 5, wherein said rotor system includes a single main rotor system.
8. The transmission gearbox as recited in claim 1, further comprising a tail drive system driven by said variable speed gearbox.
9. The transmission gearbox as recited in claim 8, wherein said tail drive system is driven from an input side of said gear path and said reduced gear path upstream of said clutch and said freewheel unit.
10. The transmission gearbox as recited in claim 9, wherein said tail drive system is an anti-torque tail rotor.
11. The transmission gearbox as recited in claim 9, wherein said tail drive system is a translational thrust system.
12. The transmission gearbox as recited in claim 8, wherein said tail drive system is driven from an output side of said gear path and said second gear reduction downstream of said clutch and said freewheel unit.
13. The transmission gearbox as recited in claim 12, wherein said tail drive system is an anti-torque tail rotor.
14. The transmission gearbox as recited in claim 12, wherein said tail drive system is a translational thrust system.
15. A rotary-wing aircraft comprising:
a main gearbox;

a variable speed gearbox in meshing engagement with said main gearbox, said variable speed gearbox including a gear path having a clutch and a reduced gear path having a freewheel unit, said main gearbox driven at a first speed in response to engagement of said clutch such that a freewheel output of said freewheel unit overruns a freewheel input of said freewheel unit, said main gearbox driven at a second speed less than said first speed in response to disengagement of said clutch such that a clutch output of said clutch rotates at a speed less than a clutch input of said clutch, said freewheel output driven by said freewheel input; and a tail drive system driven by said variable speed gearbox.
16. The rotary-wing aircraft as recited in claim 15, wherein said tail drive system is driven from said input side of said gear path and said reduced gear path upstream of said clutch and said freewheel unit.
17. The rotary-wing aircraft as recited in claim 15, wherein said tail drive system is driven from said output side of said gear path and said reduced gear path downstream of said clutch and said freewheel unit.
18. A method of controlling a speed of a main rotor system of a rotary-wing aircraft comprising the steps of:

(1) engaging a clutch;

(2) overrunning a freewheel output over a freewheel input of a freewheel unit in response to said step (1) to drive a main gearbox of the main rotor system at a first speed;

(3) disengaging the clutch; and (4) running a clutch input separately from a clutch output in response to said step (3) to drive the main gearbox of the main rotor system at a second speed through the freewheel unit.
19. A method as recited in claim 18, wherein said step (4) further comprises:

(a) driving an output of a gear path and an output of a reduced gear path at a speed equivalent to the freewheel output to drive the main gearbox of the rotor system at the second speed.
20. A method as recited in claim 18, wherein said step (4) further comprises:

(b) driving the clutch output at a speed equivalent to the output of the gear path, the output of the reduced gear path and the freewheel output.
21. A method as recited in claim 18, wherein said step (4) further comprises:
(b) driving a clutch input at a speed equivalent to an engine.
22. A method as recited in claim 18, wherein said step (4) further comprises:
(a) driving the freewheel output by the freewheel input.
CA2609923A 2005-05-31 2006-04-28 Variable speed transmission for a rotary wing aircraft Expired - Fee Related CA2609923C (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US11/141,631 US7296767B2 (en) 2005-05-31 2005-05-31 Variable speed transmission for a rotary wing aircraft
US11/141,631 2005-05-31
PCT/US2006/016613 WO2007086906A2 (en) 2005-05-31 2006-04-28 Variable speed transmission for a rotary wing aircraft

Publications (2)

Publication Number Publication Date
CA2609923A1 true CA2609923A1 (en) 2007-08-02
CA2609923C CA2609923C (en) 2010-06-29

Family

ID=37463583

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2609923A Expired - Fee Related CA2609923C (en) 2005-05-31 2006-04-28 Variable speed transmission for a rotary wing aircraft

Country Status (6)

Country Link
US (3) US7296767B2 (en)
EP (1) EP1893486B1 (en)
JP (1) JP4681048B2 (en)
CN (1) CN101495374B (en)
CA (1) CA2609923C (en)
WO (1) WO2007086906A2 (en)

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Also Published As

Publication number Publication date
US7628355B2 (en) 2009-12-08
US20060269414A1 (en) 2006-11-30
CN101495374B (en) 2015-07-22
JP4681048B2 (en) 2011-05-11
CA2609923C (en) 2010-06-29
WO2007086906A2 (en) 2007-08-02
US20100044498A1 (en) 2010-02-25
EP1893486A4 (en) 2013-04-24
EP1893486A2 (en) 2008-03-05
WO2007086906A3 (en) 2009-04-23
CN101495374A (en) 2009-07-29
US7296767B2 (en) 2007-11-20
US7942365B2 (en) 2011-05-17
JP2008545578A (en) 2008-12-18
EP1893486B1 (en) 2017-01-11
US20080173752A1 (en) 2008-07-24

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