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Home , Accessory drive

(19) TZZ ZZ_T

(11) EP 2 060 759 B1

(12) EUROPEAN PATENT SPECIFICATION

(45) Date of publication and mention (51) Int Cl.: of the grant of the patent: F02C 7/32 (2006.01) F02C 7/36 (2006.01) 27.01.2016 Bulletin 2016/04

(21) Application number: 08253726.7

(22) Date of filing: 14.11.2008

(54) with two accessory drive gearboxes Gasturbine mit zwei Nebenaggregategetriebe Turbine à gaz avec deux boîtiers d’entraînement d’accessoires

(84) Designated Contracting States: (74) Representative: Leckey, David Herbert DE GB Dehns St Bride’s House (30) Priority: 14.11.2007 US 939725 10 Salisbury Square London (43) Date of publication of application: EC4Y 8JD (GB) 20.05.2009 Bulletin 2009/21 (56) References cited: (73) Proprietor: United Technologies Corporation WO-A1-95/02120 WO-A1-2005/005810 Hartford, CT 06101 (US) US-A1- 2007 157 597

(72) Inventor: Chaudhry, Zarffir A. South Glastonbury, Connecticut 06073 (US)

Note: Within nine months of the publication of the mention of the grant of the European patent in the European Patent Bulletin, any person may give notice to the European Patent Office of opposition to that patent, in accordance with the Implementing Regulations. Notice of opposition shall not be deemed to have been filed until the opposition fee has been paid. (Art. 99(1) European Patent Convention). EP 2 060 759 B1

Printed by Jouve, 75001 PARIS (FR) 1 EP 2 060 759 B1 2

Description Figure 1 is a highly schematic view of a gas turbine engine. BACKGROUND Figure 2a is a schematic view of a first accessory drive gearbox associated with the engine shown in [0001] This disclosure relates to a gas turbine gearbox 5 Figure 1. arrangement that is used to support and rotationally drive Figure 2b is a schematic view of a second accessory accessory drive components, such as a fuel pump, hy- drive gearbox associated with the engine shown in draulic pump, generator, lubrication pump and/or starter. Figure 1. [0002] Gas turbine engines for commercial aircraft ap- plications typically include an engine core housed within 10 DETAILED DESCRIPTION a core nacelle. In one type of arrangement known as a turbofan engine, the core drives a large fan upstream [0009] An engine 10 with geared architecture is shown from the core that provides airflow into the core. One or in Figure 1. A pylon secures the engine 10 to an aircraft. more spools are arranged within the core, and a The engine 10 includes a core nacelle 12 that surrounds train may be provided between one of the spools and the 15 a low spool 14 and high spool 24 that are rotatable about fan. A fan case and nacelle surround the fan and at least a common axis A. The low spool 14 supports a low pres- a portion of the core. sure compressor 16 and low pressure turbine 18. In the [0003] An inlet of the fan nacelle is designed to avoid example, the low spool 14 drives a fan 20 through a gear flow separation. At cruise conditions, a thinner inlet lip is train 22. The high spool 24 supports a high pressure com- desired to minimize drag and increase fuel economy. The 20 pressor 26 and high pressure turbine 28. A nacelles are sized to accommodate the widest section 30 is arranged between the high pressure compressor of engine, which is often dictated by the size of a single 26 and high pressure turbine 28. Compressed air from accessory drive gearbox. The accessory drive gearbox, compressors 16, 26 mixes with fuel from the combustor which is driven by a spool through a radial tower shaft 30 and is expanded in turbines 18, 28. and angle gearbox, is typically contained within either 25 [0010] In the example shown, the engine 10 is a high the fan nacelle or the core nacelle. A fuel pump, hydraulic bypass turbofan arrangement. In one example, the by- pump, generator, lubrication pump, starter and numer- pass ratio is greater than 10, and the turbofan diameter ous other components are typically mounted to the same is substantially larger than the diameter of the low pres- accessory drive gearbox, which takes up significant sure compressor 16. The low pressure turbine 18 has a space. As a result, the diameter of the nacelle housing 30 pressure ratio that is greater than 5:1, in one example. the accessory drive gearbox and accessory components The gear train 22 is an epicycle gear train, for example, must be increased beyond a desired size. The larger di- a star gear train, providing a gear reduction ratio of great- ameter nacelle results in a thicker inlet lip thereby in- er than 2.5:1. It should be understood, however, that the creasing drag at cruise conditions. Increased nacelle di- above parameters are only exemplary of a contemplated ameter also increases weight and fuel consumption.35 geared architecture engine. That is, the invention is ap- What is needed is a gas turbine engine design with a plicable to other engines including direct drive . reduced diameter nacelle. [0011] Airflow enters a fan nacelle 34, which surrounds [0004] Gas turbine engines having multiple gearboxes the core nacelle 12 and fan 20. The fan 20 directs air into rotationally coupled to at least one spool of the engine the core nacelle 12, which is used to drive the turbines are disclosed in WO 95/02120 A1 and WO 2005/005810 40 18, 28, as is known in the art. Turbine exhaust exits the A1. core nacelle 12 once it has been expanded in the turbines 18, 28, in a passage provided between the core nacelle SUMMARY 12 and a tail cone 32. [0012] A core housing 11 is arranged within the core [0005] The present invention provides a gas turbine 45 nacelle 12 and is supported within the fan nacelle 34 by engine as set forth in claim 1. structure 36, such as flow exit guide vanes, extending [0006] The accessory drive components are split be- radially inwardly from a fan case 35. A generally annular tween the two gearboxes to reduce the diameter of the bypass flow path 38 is arranged between the core and nacelle adjacent to each gearbox, enabling the design fan nacelles 12, 34. The examples illustrated in the Fig- of slimmer nacelles and more efficient engines. 50 ures depict a high bypass flow arrangement in which ap- [0007] These and other features of the disclosure can proximately eighty percent of the airflow entering the fan be best understood from the following specification and nacelle 34 bypasses the core nacelle 12. The bypass drawings, the following of which is a brief description. flow within the bypass flow path 38 exits the fan nacelle 34 through a fan nozzle exit area at the aft of the fan BRIEF DESCRIPTION OF THE DRAWINGS 55 nacelle 34. [0013] In the example shown in Figure 1, at least two [0008] accessory drive gearboxes 40, 140 are used to drive ac- cessory components at different location within the en-

2 3 EP 2 060 759 B1 4 gine. Instead of the single accessory drive gearbox typ- 140) being rotationally coupled to the low and ically used, the work can be split between the gearboxes high spools (14, 24), respectively; 40, 140 to reduce the size of each gearbox and, thus, core and fan nacelles (12, 34), the core nacelle the size of the associated nacelle. Example accessory (12) surrounding the at least one spool (14, 24), drive components are: a fuel pump 42, hydraulic pump 5 the fan nacelle (34) surrounding the core nacelle 44, generator 46, lubrication pump 48, starter 50 and (12) to provide a bypass flow path between the other accessory drive components 53. nacelles (12, 34), and the accessory drive gear- [0014] In one example, one accessory drive gearbox boxes (40, 140); 40 is arranged in a radial space between the fan case 35 a fan case (35) surrounding a fan (20) that is and an exterior surface 33 of the fan nacelle 34. The10 arranged upstream from the core nacelle (12), other accessory drive gearbox 140 is arranged in a radial and a core housing (11) arranged about the at space between the core housing 11 and an exterior sur- least one spool (14, 24), the accessory drive face 13 of the core nacelle 12. The accessory drive gear- gearboxes (40, 140) supported by at least one boxes are axially and radially spaced from one another, of the fan case (35) and the core housing (11), which enables desired packaging of the gearboxes. 15 the corenacelle (12) being arrangedradially out- [0015] Referring to Figures 1 and 2a, the accessory wardly of the core housing (11) providing a first drive gearbox 40 is driven by the low spool 14. The low radial space there between, and the fan nacelle spool 14 is coupled to a tower shaft 62 with bevel , (34) is arranged radially outwardly of fan case as is known. The tower shaft 62 drives an input shaft 52 (35) providing a second radial space there be- through an angle gearbox 64, which is mounted to the 20 tween; fan case 35, for example. The accessory drive gearbox accessory drive components including at least 40 is supported by the fan case 35, and receives rota- two of a fuel pump (42), a generator (46), a lu- tional drive from the input shaft 52. The accessory com- brication pump (48), or a starter (50); and ponents shown mounted on the accessory drive gear- wherein one of the accessory components is boxes 40, 140 are exemplary only and may be different 25 mounted to and driven by the first accessory than depicted in the Figures. The accessory components drive gearbox (40), and another of the accessory for each gearbox are selected, for example, based upon components is mounted to and driven by the packaging considerations and the desired rotational second accessory drive gearbox (140), the first speed of the accessory component. In the example and second accessory drive gearboxes (40, shown in Figure 1, the accessory drive gearboxes 40, 30 140) being arranged within the first and second 140 are respectively driven by the low and high spools radial spaces, respectively. 14, 24 to provide the desired rotational speed to acces- sory drive components associated with the gearboxes. 2. The turbine engine according to claim 1, wherein the [0016] Referring to Figure 2b, the accessory drive core and fan nacelles (12, 34) each include exterior gearbox 140 is driven by the high spool 24. The high35 surfaces (13, 33), the accessory drive gearboxes spool 24 is coupled to a tower shaft 162 with bevel gears. (40, 140) and their respective accessory drive com- The tower shaft 162 drives an input shaft 152 through an ponents (42 ...50) contained radially within the exte- angle gearbox 164, which is mounted to the core housing rior surfaces (13, 33). 11, for example. The accessory drive gearbox 140 is sup- ported by the core housing 11, and receives rotational 40 3. Theturbine engine accordingto any preceding claim, drive from the input shaft 152. wherein the first and second accessory drive gear- [0017] Although an example embodiment has been boxes (40, 140) are axially spaced from one another. disclosed, a worker of ordinary skill in this art would rec- ognize that certain modifications would come within the 4. Theturbine engine accordingto any preceding claim, scope of the claims. For that reason, the following claims 45 wherein at least one of the accessory drive gearbox- should be studied to determine their true scope and con- es (40, 140) is coupled to the at least one spool (14, tent. 24) by a tower shaft (62, 162), angle box (64, 164) and input shaft (52, 152), the angle box (64, 164) interconnected between the tower (62, 162) and in- Claims 50 put (64, 164) shafts.

1. A turbine engine (10) comprising: Patentansprüche first and second accessory drive gearboxes (40, 140) rotationally coupled to at least one spool 55 1. Turbinenmotor (10), umfassend: (14; 24) which includes low and high spools (14, 24) rotatable about a common axis (A), the first ein erstes und ein zweites Nebenaggregatge- and second accessory drive gearboxes (40, triebe (40, 140), die an mindestens eine Spule

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(14, 24) drehgekoppelt sind, die niedrige und gekoppelt ist, wobei das Winkelgetriebe (64, 164) hohe, um eine gemeinsame Achse (A) drehbare zwischen den Turm- (62, 162) und Eingangswellen Spulen (14, 24) umfasst, wobei das erste und (64, 164) eingebunden ist. zweiteNebenaggregatgetriebe (40, 140)jeweils an die niedrigen und hohen Spulen (14, 24)5 drehgekoppelt sind; Revendications Kern- und Lüftungsgondeln (12, 34), wobei die Kerngondel (12) die mindestens eine Spule (14, 1. Moteur à turbine (10) comprenant : 24) und die Lüftungsgondel (34) die Kerngondel (12) umgibt, um einen Bypass-Strömungsweg 10 de première et deuxième boîtiers d’entraîne- zwischen den Gondeln (12, 34) und den Nebe- ment d’accessoires (40, 140) couplées en rota- naggregatgetrieben (40, 140) zu schaffen; tion à au moins un tambour (14, 24) qui contient ein Lüftungsgehäuse (35), das eine Lüftung (20) des tambours bas et hauts (14, 24) pouvant tour- umgibt, die der Kerngondel (12) vorgelagert ist, ner autour d’un axe commun (A), les première und ein Kerngehäuse (11), das um die mindes- 15 et deuxième boîtiers d’entraînement d’acces- tens eine Spule (14, 24) angeordnet ist, wobei soires (40, 140) étant couplées en rotation aux die Nebenaggregatgetriebe (40, 140) von min- tambours bas et hauts (14, 24), destens einem von dem Lüftungsgehäuse (35) respectivement ; und dem Kerngehäuse (11) getragen werden, des nacelles centrale et de ventilateur (12, 34), und die Kerngondel (12) von dem Kerngehäuse 20 la nacelle centrale (12) entourant l’au moins un (11) radial nach außen angeordnet ist, wodurch tambour (14, 24), la nacelle de ventilateur (34) ein erster radialer Raum dazwischen geschaf- entourant la nacelle centrale (12) pour produire fen wird, und die Lüftungsgondel (34) von dem un écoulement de contournement entre les na- Lüftungsgehäuse (35) radial nach außen ange- celles (12, 34) et les boîtiers d’entraînement ordnet ist, wodurch ein zweiter radialer Raum 25 d’accessoires (40, 140) ; dazwischen geschaffen wird; un carter de ventilateur (35) entourant un venti- Nebenaggregatgetriebeelemente, lateur(20) qui estdisposé enamont de lanacelle einschließlich mindestens zwei der Folgenden: centrale (12), et un carter central(11) disposé einer Treibstoffpumpe (42), eines Generators autour du tambour (14, 24) au nombre d’au (46), einer Schmierpumpe (48) oder eines An- 30 moins un, les boîtiers d’engrenages d’accessoi- lassers (50); und res (40, 140) soutenues par le carter de venti- wobei eines der Nebenaggregatgetriebeele- lateur (35) au nombre d’au moins un et le carter mente an dem ersten Nebenaggregatgetriebe centrale (11), la nacelle de coeur (12) étant dis- (40) befestigt ist und von diesem angetrieben posés radialement vers l’extérieur du carter cen- wird, und ein anderes der Nebenaggregatgetrie- 35 trale (11), ce qui donne un premier espace radial beelemente an dem zweiten Nebenaggregatge- entre eux, et la nacelle de ventilateur (34) est triebe (140) befestigt ist und von diesem ange- disposée radialement vers l’extérieur du carter trieben wird, wobei das erste und zweite Nebe- de ventilateur (35), ce qui crée un deuxième es- naggregatgetriebe (40, 140) jeweils in dem ers- pace radial entre eux ; ten und zweiten radiale Raum angeordnet sind. 40 les composants d’entraînement d’accessoires comprenant au moins deux éléments parmi une 2. Turbinenmotor nach Anspruch 1, wobei die Kern- pompe à combustible (42), un générateur (46), und Lüftungsgondeln (12, 34) jeweils äußere Ober- une pompe de lubrification (48) ou un démarreur flächen (13, 33) aufweisen, wobei die Nebenaggre- (50) ; et gatgetriebe (40, 140) und ihre jeweiligen Nebenag- 45 un des composants accessoires étant monté au gregatgetriebeelemente (42 ...50) radial innerhalb premier boîtier d’entraînement d’accessoires der äußeren Oberflächen (13, 33) enthalten sind. (40), tandis qu’un autre des composants acces- soires est monté au deuxième boîtier d’entraî- 3. Turbinenmotor nach einem der vorangehenden An- nement d’accessoires (140) et entraîné par cel- sprüche, wobei das erste und zweite Nebenaggre- 50 le-ci, les première et deuxième boîtiers d’entraî- gatgetriebe (40, 140) axial voneinander beabstandet nement d’accessoires (40, 140) étant disposées sind. dans les premier et deuxième espaces radiaux, respectivement. 4. Turbinenmotor nach einem der vorangehenden An- sprüche, wobei mindestens eines der Nebenaggre- 55 2. Moteur à turbine selon la revendication 1, dans le- gatgetriebe (40, 140) an die mindestens eine Spule quel les nacelles centrale et de ventilateur (12, 34) (14, 24) durch eine Turmwelle (62, 162), ein Winkel- comprennent chacune des surfaces extérieures (13, getriebe (64, 164) und eine Eingangswelle (52, 152) 33), les boîtiers d’entraînement d’accessoires (40,

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140) et leurs composants d’entraînement d’acces- soires respectifs (42, ...50) contenus radialement à l’intérieur des surfaces extérieures (13, 33).

3. Moteur à turbine selon l’une quelconque des reven- 5 dications précédentes, dans lequel les première et deuxième boîtes d’entraînement d’accessoires (40, 140) sont espacées axialement l’une de l’autre.

4. Moteur à turbine selon l’une quelconque des reven- 10 dicationsprécédentes, dans lequel au moinsl’un des boîtiers d’entraînement d’accessoires (40, 140) est couplé à l’au moins un tambour (14, 24) par un arbre de tour (62, 162), une boîte d’angle (64, 164) et un arbre d’entrée (52, 152), la boîte d’angle (64, 164) 15 étant interconnectée entre les arbres de tour (62, 162) et d’entrée (64, 164).

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REFERENCES CITED IN THE DESCRIPTION

This list of references cited by the applicant is for the reader’s convenience only. It does not form part of the European patent document. Even though great care has been taken in compiling the references, errors or omissions cannot be excluded and the EPO disclaims all liability in this regard.

Patent documents cited in the description

• WO 9502120 A1 [0004] • WO 2005005810 A1 [0004]

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