EP1711700A1 - Configuration compacte pour fixer une pompe carburant ou un autre accessoire a un boitier d'entrainement des accessoires - Google Patents

Configuration compacte pour fixer une pompe carburant ou un autre accessoire a un boitier d'entrainement des accessoires

Info

Publication number
EP1711700A1
EP1711700A1 EP05706407A EP05706407A EP1711700A1 EP 1711700 A1 EP1711700 A1 EP 1711700A1 EP 05706407 A EP05706407 A EP 05706407A EP 05706407 A EP05706407 A EP 05706407A EP 1711700 A1 EP1711700 A1 EP 1711700A1
Authority
EP
European Patent Office
Prior art keywords
accessory
gearbox
gas turbine
turbine engine
casing
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.)
Withdrawn
Application number
EP05706407A
Other languages
German (de)
English (en)
Inventor
James Robert Jarvo
Salvatore Calandra
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.)
Pratt and Whitney Canada Corp
Original Assignee
Pratt and Whitney Canada Corp
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 Pratt and Whitney Canada Corp filed Critical Pratt and Whitney Canada Corp
Publication of EP1711700A1 publication Critical patent/EP1711700A1/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user

Definitions

  • the present invention relates to gas turbine engines and, more particularly, to configurations for connecting fuel pumps or other accessories to accessory gearboxes.
  • a fuel-metering unit 20 such as a cartridge fuel pump
  • the accessory gearbox 30 has an enclosed casing 34 which houses a reduction gear set 36.
  • the reduction gear set 36 is driven by a drive gear 40, which is mounted to a starter shaft 42 rotatably secured by a bearing mount 44.
  • the reduction gear set 36 is affixed to the shaft 32 whose internal splines 33 are in meshing engagement with the external splines of a complementarily shaped stub shaft 22 protruding from a casing 24 of the fuel-metering unit 20.
  • the fuel-metering unit 20 has a flanged pad 26 which abuts a corresponding flanged pad 46 on the accessory gearbox 30.
  • a gas turbine engine accessory in combination with a gearbox of a gas turbine engine, the accessory being removably mounted to the gearbox and having an integral drive shaft extending into the gearbox, and a driven gear mounted on the drive shaft, the driven gear being adapted to directly engage a drive gear of said gearbox.
  • a gas turbine engine driving arrangement comprising a gas turbine engine accessory integrated to an accessory gearbox, the accessory comprising an open-ended accessory casing, the open-ended accessory casing being adapted to be removably mounted to an accessory gearbox casing having a complementary opening, the accessory casing and gearbox casing mating to fo ⁇ ri a fully enclosed unit.
  • a gas turbine engine comprising at least a compressor, a combustor adapted to receive compressed air from the compressor, a turbine for extracting power from the combustion gases leaving the combustor, an accessory gearbox having at least one drive gear driven by the turbine; and at least one gas turbine engine accessory removably mounted to the accessory gearbox, the accessory having at least one drive shaft with at least one driven gear mounted to the drive shaft, the driven gear meshing with the drive gear of the accessory gearbox.
  • Fig. 1 is a schematic cross-sectional view of a gas turbine engine to which an embodiment of the present invention is applied;
  • Fig. 2 is a cross-sectional view of a compact configuration of a fuel- metering unit and accessory gearbox in accordance with an embodiment of the present invention.
  • Fig. 3 is a cross-sectional view of a prior-art configuration of a fuel- metering unit and accessory gearbox.
  • Fig. 1 illustrates a gas turbine engine 10 of a type preferably provided for use in subsonic flight, generally comprising in serial flow communication a fan 12 through which ambient air is propelled, a multistage compressor 14 for pressurizing the air, a combustor 16 in which the compressed air is mixed with fuel and ignited for generating an annular stream of hot combustion gases, and a turbine section 18 for extracting energy from the combustion gases.
  • the turbine section 18 drives various accessories, such as a fuel pump, oil pump, hydraulic pump, air pump, or electric generator, via an accessory gearbox 30' (Fig.2).
  • Fig. 2 illustrates an embodiment of the present invention in which a fuel-metering unit 20', in this application called a 'cartridge fuel pump', is partially embedded in the accessory gearbox 30'.
  • the fuel-metering unit 20' and the accessory gearbox 30' are partially encased within an accessory casing 24' and a gearbox casing 34', respectively.
  • the accessory casing 24' and the gearbox casing 34 have complementary openings so that a portion of the fuel-metering unit 20 can be inserted, or "embedded", in the accessory gearbox 30' (which acts like a receptacle or socket).
  • a spigot or peripheral portion 60 of the unit 20' is adapted to matingly engage at least one of the casings 24' and 34, and an appropriate seal member 62 is provided to seal the connection (an 'o-ring' type seal 62 is shown, although other suitable seal types, such as face seals or other seals, may be employed).
  • an 'o-ring' type seal 62 is shown, although other suitable seal types, such as face seals or other seals, may be employed.
  • an embedded portion 50 represents about one half of the length of the cartridge fuel pump, although it should be appreciated that the degree to which the accessory is embedded in the accessory gearbox 30' will vary according to design exigencies, such as the depth inside the accessory gearbox of a drive gear that is to mesh with a driven gear of the accessory.
  • a sufficient amount of the accessory is embedded in the gearbox to permit a portion of the accessory casing to be absent, so that the accessory is open casing to be closed by assembly with the gearbox.
  • the fuel-metering unit 20' (the cartridge fuel pump in this example) is powered by a drive shaft 35. Affixed to the drive shaft 35 is a reduction gear set 36'.
  • the reduction gear set 36' has a driven gear 36a' and a spacer gear 36b'.
  • the driven gear 36a' meshes with, and is driven by, a drive gear 40' mounted to a starter shaft 42' which is, in turn, rotatably secured by a bearing mount 44'.
  • the spacer gear 36b' is in meshing engagement with a stationary gear 37 provided in the gearbox casing 34' for ensuring proper alignment of the drive shaft 35 so that torque imparted to the driven gear 36a' by the drive gear 40' does not cause the drive shaft
  • the drive gear 40' may be connected to any accessory drive shaft that receives torque from the turbine shaft.
  • the drive shaft 35 is preferably not a splined set, but rather a single or integral shaft extending into the unit 20' and to which the gear 36a' is affixed, such that gear set 36 drives the unit 20' directly. This aspect contributes to the weight savings in the concept, as will be discussed further below.
  • the partial embedding of the fuel-metering unit 20' in the accessory gearbox 30' results in a compact and lightweight configuration. Not only are weight and overhung moment reduced, but so is the number of parts.
  • the drive shaft 35 of the unit 20' is directly connected to the reduction gear set 36.
  • the splined shaft 32 (shown in Fig. 3) is thus eliminated, as are the flanged pads 26, 46.
  • the fuel- metering unit 20' and the accessory gearbox 30' are not individually fully encased, the amount of casing material required is also reduced.
  • this compact configuration can be advantageously used on gas turbine engines of all sizes and all types to reduce weight, overhung moment and complexity.
  • the fuel-metering unit 20' may further be provided with a mounting face (in this case, above the spigot) to abut the casing 34' of the gearbox 30'. Suitable fasteners (not shown) secure the device to the gearbox.
  • the drive shaft 35 and reduction gear set 36' extend below the mounting face by a predetermined distance calculated to ensure that the driven gear 36a' mounted to the drive shaft 35 meshes with the drive gear 40' of the accessory gearbox 30'.
  • the fuel-metering unit 20' may also include a spigot 60 having a circular lip integrally formed with the mounting face for centering the fuel- metering unit 20' with respect to the accessory gearbox 30'.
  • the rotation of the turbine shaft drives the accessory gearbox 30' which, in turn, powers the embedded cartridge fuel pump (or other fuel-metering unit) 20.
  • the cartridge fuel pump, or other fuel-metering unit pumps fuel to a plurality of fuel injectors which inject the fuel into the combustor 16 where the fuel and compressed air from the compressor 14 are combusted to generate hot gases. These hot gases impinge on a plurality of turbine blades which drive the turbine shaft.
  • the rotation of the turbine shaft powers the cartridge fuel pump 20' via the accessory gearbox 30'.
  • the embedded accessory could be an oil pump, a hydraulic pump, an air pump, or an electric generator (this is not intended to be an exhaustive list), hi each case, the drive shaft of the accessory is provided with a reduction gear set or a driven gear for meshing with a drive gear of the accessory gearbox.
  • the drive shaft of the accessory is provided with a reduction gear set or a driven gear for meshing with a drive gear of the accessory gearbox.
  • other accessories may also be embedded within an accessory gearbox in the manner described.
  • the embodiments of the invention described above are intended to be exemplary.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Selon l'invention, un accessoire de turbine à gaz (20') est monté amovible sur un boîtier d'entraînement (30') d'une turbine à gaz (10). L'accessoire présente un arbre d'entraînement (35) s'étendant dans le boîtier d'entraînement (30'). Une roue menée (36a') est montée sur l'arbre d'entraînement (35). La roue menée (36a') est conçue pour venir en prise directement avec une roue menante (40') du boîtier d'entraînement (30'). Le but de ladite conception améliorée est d'alléger le poids total de la turbine à gaz par réduction du nombre de ses éléments et composants.
EP05706407A 2004-01-30 2005-01-24 Configuration compacte pour fixer une pompe carburant ou un autre accessoire a un boitier d'entrainement des accessoires Withdrawn EP1711700A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US76684704A 2004-01-30 2004-01-30
PCT/CA2005/000077 WO2005073540A1 (fr) 2004-01-30 2005-01-24 Configuration compacte pour fixer une pompe carburant ou un autre accessoire a un boitier d'entrainement des accessoires

Publications (1)

Publication Number Publication Date
EP1711700A1 true EP1711700A1 (fr) 2006-10-18

Family

ID=34826526

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05706407A Withdrawn EP1711700A1 (fr) 2004-01-30 2005-01-24 Configuration compacte pour fixer une pompe carburant ou un autre accessoire a un boitier d'entrainement des accessoires

Country Status (4)

Country Link
EP (1) EP1711700A1 (fr)
JP (1) JP2007519848A (fr)
CA (1) CA2554509A1 (fr)
WO (1) WO2005073540A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10995675B2 (en) 2019-02-19 2021-05-04 Pratt & Whitney Canada Corp. Gas turbine engine with accessory gearbox

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7495361B2 (en) * 2004-11-05 2009-02-24 Pratt & Whitney Canada Corp. Electric machine arrangement
US8172512B2 (en) * 2008-04-23 2012-05-08 Hamilton Sundstrand Corporation Accessory gearbox system with compressor driven seal air supply
JP5016706B2 (ja) * 2009-11-04 2012-09-05 川崎重工業株式会社 航空機用始動発電装置
FR2953199B1 (fr) * 2009-12-02 2012-02-24 Hispano Suiza Sa Alterno-demarreur de moteur aeronautique entraine par un train epicycloidal
US8857192B2 (en) 2010-04-20 2014-10-14 General Electric Company Accessory gearbox with a starter/generator
US20120006137A1 (en) * 2010-07-07 2012-01-12 Hamilton Sundstrand Corporation Gear driven accessory for gearbox
US9650964B2 (en) 2010-12-28 2017-05-16 General Electric Company Accessory gearbox with a starter/generator
ITFI20110247A1 (it) * 2011-11-14 2013-05-15 Nuovo Pignone Spa "device and method for slow turning of an aeroderivative gas turbine"
FR3007462B1 (fr) * 2013-06-21 2017-11-24 Hispano-Suiza Boitier d'accessoires de turbomachine equipe d'une pompe centrifuge
US10316898B2 (en) 2016-01-28 2019-06-11 Ge Aviation Systems Llc Method and disconnector for disconnecting a drive shaft

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4525995A (en) * 1983-04-04 1985-07-02 Williams International Corporation Oil scavening system for gas turbine engine
EP0540192A1 (fr) * 1991-10-30 1993-05-05 General Electric Company Plaque de montage pour entraînement d'accessoires
US6058791A (en) * 1998-03-19 2000-05-09 Alliedsignal, Inc. Accessory mechanical drive for a gas turbine engine
JP2003269192A (ja) * 2002-03-18 2003-09-25 Ishikawajima Harima Heavy Ind Co Ltd ガスタービンエンジン用ラジアルドライブシャフトの軸受け装置

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2005073540A1 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10995675B2 (en) 2019-02-19 2021-05-04 Pratt & Whitney Canada Corp. Gas turbine engine with accessory gearbox
US11326523B2 (en) 2019-02-19 2022-05-10 Pratt & Whitney Canada Corp. Gas turbine engine with accessory gearbox

Also Published As

Publication number Publication date
CA2554509A1 (fr) 2005-08-11
JP2007519848A (ja) 2007-07-19
WO2005073540A1 (fr) 2005-08-11

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