WO2005120949A3 - Small-size high-speed transmission system for use in microturbine-powered aircraft - Google Patents

Small-size high-speed transmission system for use in microturbine-powered aircraft Download PDF

Info

Publication number
WO2005120949A3
WO2005120949A3 PCT/US2005/000127 US2005000127W WO2005120949A3 WO 2005120949 A3 WO2005120949 A3 WO 2005120949A3 US 2005000127 W US2005000127 W US 2005000127W WO 2005120949 A3 WO2005120949 A3 WO 2005120949A3
Authority
WO
WIPO (PCT)
Prior art keywords
configuration
transmission system
rpm
shaft
microturbine
Prior art date
Application number
PCT/US2005/000127
Other languages
French (fr)
Other versions
WO2005120949A2 (en
Inventor
J William Box
Jules G Kish
Original Assignee
Locust Usa Inc
J William Box
Jules G Kish
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
Priority claimed from US10/756,054 external-priority patent/US6920406B1/en
Application filed by Locust Usa Inc, J William Box, Jules G Kish filed Critical Locust Usa Inc
Publication of WO2005120949A2 publication Critical patent/WO2005120949A2/en
Publication of WO2005120949A3 publication Critical patent/WO2005120949A3/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16H—GEARING
    • F16H1/00—Toothed gearings for conveying rotary motion
    • F16H1/02—Toothed gearings for conveying rotary motion without gears having orbital motion
    • F16H1/20—Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members
    • F16H1/22—Toothed gearings for conveying rotary motion without gears having orbital motion involving more than two intermeshing members with a plurality of driving or driven shafts; with arrangements for dividing torque between two or more intermediate shafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D35/00—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions

Abstract

A transmission system that is used in conjunction with a microturbine engine for propelling an aircraft body, such as a propeller-based fixed-wing aircraft or a rotor-based vertical lift aircraft, or for a wide variety of other applications. The output shaft of the microturbine engine preferably operates at a rotational speed in a range between 72,000 RPM and 150,000 RPM with an output power between 150 HP and 5 HP (and most preferably operates in an extended range between 50,000 RPM and 200,000 RPM with an output power between 200 HP and 5 HP). The two reduction stages provide a reduction ratio preferably having a value of at least 19, and most preferably greater than 24. The transmission system is of small-size preferably having a maximum diameter less than twelve inches. The two stages of the transmission system may comprise any one (or parts of) of a number of configurations, including an in-line lay shaft configuration, an in-line star-star configuration, an offset starspur configuration, an offset compound idler configuration, an inline traction-internal gear configuration, and an inline traction-planetary gear configuration. Preferably, the input stage of the transmission system is self-equilibrating such that first shaft can be supported without bearings and is operably coupled to the output shaft of the microturbine engine by an outside diameter piloted spline coupling mechanism. For vertical lift applications, a single traction stage along with a bevel gear assembly or other shaft transmission mechanism can be used to provide the necessary RPM reduction.
PCT/US2005/000127 2004-01-12 2005-01-04 Small-size high-speed transmission system for use in microturbine-powered aircraft WO2005120949A2 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US10/756,054 2004-01-12
US10/756,054 US6920406B1 (en) 2004-01-07 2004-01-12 Method of measuring the azimuth and resetting zero azimuth automatically

Publications (2)

Publication Number Publication Date
WO2005120949A2 WO2005120949A2 (en) 2005-12-22
WO2005120949A3 true WO2005120949A3 (en) 2006-07-13

Family

ID=35503703

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2005/000127 WO2005120949A2 (en) 2004-01-12 2005-01-04 Small-size high-speed transmission system for use in microturbine-powered aircraft

Country Status (1)

Country Link
WO (1) WO2005120949A2 (en)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4177693A (en) * 1978-06-22 1979-12-11 Avco Corporation Drive system
US4301981A (en) * 1979-06-29 1981-11-24 Joseph Hartt Aircraft with rotary wing
US4856377A (en) * 1987-01-07 1989-08-15 Pratt & Whitney Canada Inc. Planetary gear system for a gas turbine engine
US5108043A (en) * 1991-03-29 1992-04-28 Bell Helicopter Textron, Inc. Twin engine helicopter accesssory drive
US5271295A (en) * 1990-12-12 1993-12-21 Aerospatiale Societe Nationale Industrielle Mechanism for transmitting power between a driving shaft and two assemblies to be driven
US5782433A (en) * 1995-04-27 1998-07-21 Advanced Technology Institute Of Commuter-Helicopter, Ltd. Engine deceleration device and power transmission device for helicopters
US6264138B1 (en) * 1998-09-18 2001-07-24 Rolls-Royce Corporation Propeller gearbox
US6302356B1 (en) * 1998-08-21 2001-10-16 Rolls-Royce Corporation Helicopter two stage main reduction gearbox

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4177693A (en) * 1978-06-22 1979-12-11 Avco Corporation Drive system
US4301981A (en) * 1979-06-29 1981-11-24 Joseph Hartt Aircraft with rotary wing
US4856377A (en) * 1987-01-07 1989-08-15 Pratt & Whitney Canada Inc. Planetary gear system for a gas turbine engine
US5271295A (en) * 1990-12-12 1993-12-21 Aerospatiale Societe Nationale Industrielle Mechanism for transmitting power between a driving shaft and two assemblies to be driven
US5108043A (en) * 1991-03-29 1992-04-28 Bell Helicopter Textron, Inc. Twin engine helicopter accesssory drive
US5782433A (en) * 1995-04-27 1998-07-21 Advanced Technology Institute Of Commuter-Helicopter, Ltd. Engine deceleration device and power transmission device for helicopters
US6302356B1 (en) * 1998-08-21 2001-10-16 Rolls-Royce Corporation Helicopter two stage main reduction gearbox
US6264138B1 (en) * 1998-09-18 2001-07-24 Rolls-Royce Corporation Propeller gearbox

Also Published As

Publication number Publication date
WO2005120949A2 (en) 2005-12-22

Similar Documents

Publication Publication Date Title
WO2005121598A3 (en) Small-size traction drive transmission system for use in microturbine-powered aircraft
US20090222178A1 (en) Power transmission gearbox presenting a modifiable speed of rotation at its outlet, and a corresponding method of operation
IL158583A0 (en) Differential electric engine with variable torque conversion
WO1999033682A3 (en) Gear box
WO2007086906A3 (en) Variable speed transmission for a rotary wing aircraft
WO2000017540A3 (en) Propeller gearbox
CN103968003A (en) Torque shunting transmission mechanism for helicopter main reducing gear
GB0412736D0 (en) An electrically driven single speed differential transmission
EP1038766A3 (en) Power transmission apparatus for helicopter
KR20160060675A (en) Vehicle traction device and vehicle incorporating same
JPS5517727A (en) Transmission with sub speed changer
CN107202139A (en) One kind becomes prompt drop square transfer case
WO2005120949A3 (en) Small-size high-speed transmission system for use in microturbine-powered aircraft
EP1295788A3 (en) Hybrid power input quill for transmissions
RU2613099C1 (en) Main reduction gear of helicopter
US20190085951A1 (en) Multi-stage transmission for vehicles
CN110319161A (en) A kind of transmission mechanism of compact-sized wide transmission ratio
US7100468B2 (en) Split torque gearbox
US10914239B2 (en) High-speed section disconnect for driven turbocharger
CN108626316A (en) A kind of dual input multi output gear-box
CN207111841U (en) A kind of large-scale single rotor plant protection unmanned plane gear case transmission mechanism
EP1593877B1 (en) Motor vehicle gearbox
CN108351005B (en) Gearbox unit for agricultural vehicles with a wide speed range
SE513133C2 (en) Vehicle gearbox with six forward gears
CN204755787U (en) Gear box

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A2

Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BW BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE EG ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NA NI NO NZ OM PG PH PL PT RO RU SC SD SE SG SK SL SM SY TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW

AL Designated countries for regional patents

Kind code of ref document: A2

Designated state(s): GM KE LS MW MZ NA SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LT LU MC NL PL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG

121 Ep: the epo has been informed by wipo that ep was designated in this application
NENP Non-entry into the national phase

Ref country code: DE

WWW Wipo information: withdrawn in national office

Country of ref document: DE

122 Ep: pct application non-entry in european phase