GB2198791A - A geared turbofan gas turbine engine with a booster compressor - Google Patents
A geared turbofan gas turbine engine with a booster compressor Download PDFInfo
- Publication number
- GB2198791A GB2198791A GB08620199A GB8620199A GB2198791A GB 2198791 A GB2198791 A GB 2198791A GB 08620199 A GB08620199 A GB 08620199A GB 8620199 A GB8620199 A GB 8620199A GB 2198791 A GB2198791 A GB 2198791A
- Authority
- GB
- United Kingdom
- Prior art keywords
- booster compressor
- fan assembly
- gear
- gas turbine
- fan
- 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- Withdrawn
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
-
- 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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
- F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
- F02K3/072—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with counter-rotating, e.g. fan rotors
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
A geared turbofan gas turbine engine comprises a core engine (12 Figure 1), a fan assembly 24 and a booster compressor 42. The fan assembly 24 is positioned upstream of the core engine and the booster compressor 42 is positioned upstream of the fan assembly 24. The fan assembly is driven by the turbines of the core engine via a gear assembly 54 and a rotor 44 of the booster compressor is driven by the turbines of the core engine. A planet carrier 62 of the gear assembly 54 is connected, at its downstream end to a core casing 22 of the core engine, at its upstream end to a stator casing 45 of the booster compressor 42. <IMAGE>
Description
A GEARED TURBOFAN GAS TURBINE ENGINE WITH A
BOOSTER COMPRESSOR
The present invention relates to turbofan gas turbine engines and is particularly concerned with geared turbofan gas turbine engines with booster compressors in which the fan is driven via a gear arrangement.
In the prior art it is known to have a turbofan gas turbine engine in which a fan is driven directly by a turbine of the core engine, and to have a booster compressor driven via a gear arrangement as disclosed in
US patent 3673802.
The booster compressor in this arrangement comprises two rotors which contra rotate, one of them being secured to the fan.
The present invention seeks to provide a turbofan gas turbine engine with a geared fan and a booster compressor in which the booster compressor has a stator.
Accordingly the present invention provides a turbofan gas turbine engine comprising a core engine, a fan assembly rotatably mounted in a fan casing and a booster compressor, the core engine comprising in flow series compressor means, combustor means and turbine means and being enclosed by a core casing, the fan assembly being positioned upstream of the core engine, the booster compressor being positioned upstream of the fan assembly and comprising a rotor carrying a plurality of blades and a coaxial surrounding stator carrying a plurality of vanes, the booster compressor rotor being driven by the turbine means, the fan assembly being driven by the turbine means via gear means, the gear means comprising a sun gear, a plurality of planet gears rotatably mounted on a planet carrier and an annulus gear, the sun gear being connected to the turbine means, the annulus gear being connected to the fan assembly and the planet carrier being connected to the booster compressor stator and the core casing.
The fan assembly may be rotatably mounted on the planet carrier.
The gear means may be a floating gear assembly.
A plurality of circumferentially arranged struts may extend radially from the core casing to a fan casing, the radially outer ends of the struts may have variable leading wedges.
The present invention will be more fully described by way of example with reference to the accompanying drawings in which.
Figure 1 is a partially cut away view of a turbofan gas turbine engine having a booster compressor and a gearing arrangement for driving the fan according to the present invention.
Figure 2 is an enlarged view of the gearing arrangement for driving the fan shown in Figure 1.
A turbofan gas turbine engine 10 according to the present invention, as shown in Figure 1 and 2, comprises a core engine 12 which comprises in flow series a compressor means 14, a combustor means 16, a turbine means 18 and an exhaust nozzle 20. The core engine 12 is quite conventional in that the compressor means 14 compresses air and supplies the compressed air into the combustion means 16. Fuel is injected into the combustion means 16 and is burnt in the compressed air to produce hot gases which expand through and drive the turbine means 18 before flowing through the exhaust nozzle 20. The turbine means 18 drive the compressor means 14 via shaft means (not shown).
The compressor means may comprise one or more compressors in flow series, for example an intermediate and high pressure compressor, and the turbine means may comprise one or more turbines, i.e. -a high pressure and low pressure turbine.
The core engine 12 is completely enclosed by a core casing 22.
A fan assembly 24 is positioned upstream of the core engine 12, and the fan assembly 24 comprises a plurality of fan blades 26 arranged circumferentially on and secured to a rotor 28. The rotor 28 is formed by an outer ring structure 30, which carries the fan blades 26, and an inner ring structure 32 and a plurality of guide vanes 34 which extend radially between the inner and outer ring structures 32 and 30 respectively. The fan blades 26 rotate within a fan duct 36 defined by a fan casing 38, and the fan casing 38 is secured to the core casing 22 by a plurality of circumferentially arranged radially extending struts 40.
A booster compressor 42 is positioned upstream of the fan assembly 24 and comprises a rotor 44 and a stator casing 48. The rotor 44 has a plurality of stages of blades 46, the blades in each stage are arranged circumferentially on the rotor and extend radially outwardly therefrom. The stator casing has a plurality of stages of vanes 50, the vanes in each stage are arranged circumferentially on the stator casing and extend radially inwardly therefrom. The rotor 44 and stator casing 48 are coaxial and the stator casing encloses the rotor.
A shaft 52, which may be the shaft interconnecting the intermediate pressure compressor and the low pressure turbine, is connected to and allows the turbine means to drive the rotor 44 of the booster compressor 42.
A gear assembly 54 is arranged to drive the fan assembly 24, and the gear assembly 54 comprises a sun gear 56 driven by the turbine means via the shaft 52, a plurality of planet gears 58 meshing with and driven by the sun gear 56 and an annulus gear 60 meshing with and driven by the planet gears 58. The sun gear is connected to the shaft, the annulus gear is connected to the fan assembly, and the planet gears 58 are rotatably mounted on a planet carrier 62. The planet carrier 62 is connected at its downstream end to the core casing 22 by a plurality of struts 64 which extend across a duct 74, which supplies air from the booster compressor 42 to the core engine 12.
The planet carrier 62 is connected at its upstream end to the stator casing 48 of the booster compressor 42 by the downstream stage of vanes 50 and an internal static structure 66.
The fan assembly 24 is rotatably mounted on the planet carrier 62 by bearings 68 and 70, and a bearing 72 is provided between the internal static structure 66 and the shaft 52 to support the shaft 52 at its upstream end.
A bevel gear 78 is provided on the shaft 52 to drive one or more bevel gears 76 arranged on shafts 74. The shafts 74 extend through the struts 64 to drive engine accessories or other accessories (not shown) mounted on the core engine casing 22, or extend through strut 40 to drive engine accessories or other accessories (not shown) on the fan casing 38, or a combination of both may be provided.
In operation the booster compressor rotor 44 is driven in the same direction as the turbine means 18 by the shaft 52, but the gear assembly 54 drives the fan assembly 24 in the opposite direction to the turbine means 18, core engine and the booster compressor rotor 44.
The fan assembly will rotate at a slower speed than the booster rotor, and this reduces the top speed of the fan and so reduces the noise generated by the fan.
The fan blades may be of the variable pitch type, and they may be driven to vary the pitch of the blades by any suitable variable pitch means, for example electric or electromechanical motors, and the pitch changing means is positioned in the outer ring structure 30 of the rotor.
The gear assembly may be a floating gear arrangement to achieve equal load sharing between the planet gears, and may comprise flexible connections between the annulus gear and the fan assembly.
The struts 40 may be provided at their radially outer ends with variable leading or upstream edges, and this may be achieved by providing a pivotable portion 76.
By connecting the planet carrier at its upstream end to the stator casing of the booster compressor, the need for struts extending across the fan duct from the fan casing to the stator casing is removed. This then removes the possibility of disturbances introduced into the air flowing through the fan duct to the fan.
The stages of vanes 50 of the booster compressor may be of the static or variable type, but the use of a stator assembly in the booster enables the use of variable vanes.
Claims (5)
1. A turbofan gas turbine engine comprising a core engine, a fan assembly rotatably mounted in a fan casing and a booster compressor, the core engine comprising in flow series compressor means, combustor means and turbine means and being enclosed by a core casing, the fan assembly being positioned upstream of the core engine, the booster compressor being positioned upstream of the fan assembly and comprising a rotor carrying a plurality of blades and a coaxial surrounding stator carry a plurality of vanes, the booster compressor rotor being driven by the turbine means, the fan assembly being driven by the turbine means via gear means, the gear means comprising a sun gear, a plurality of planet gears rotatably mounted on a planet carrier and an annulus gear, the sun gear being connected to the turbine means, the annulus gear being connected to the fan assembly and the planet carrier being connected to the booster compressor stator and the core casing.
2. A turbofan gas turbine engine as claimed in claim 1 in which the fan assembly is rotatably mounted on the planet carrier.
3. A turbofan gas turbine engine as claimed in claim 1 or claim 2 in which the gear means is a floating gear arrangement.
4. A turbofan gas turbine engine as claimed in claim 1, claim 2 or claim 3 in which a plurality of circumferentially arranged struts extend radially from the core casing to a fan casing, the radially outer ends of the struts having variable leading edges.
5. A turbofan gas turbine engine substantially as hereinbefore described with reference to and as shown in the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB08620199A GB2198791A (en) | 1986-08-20 | 1986-08-20 | A geared turbofan gas turbine engine with a booster compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB08620199A GB2198791A (en) | 1986-08-20 | 1986-08-20 | A geared turbofan gas turbine engine with a booster compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB8620199D0 GB8620199D0 (en) | 1986-10-01 |
| GB2198791A true GB2198791A (en) | 1988-06-22 |
Family
ID=10602937
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08620199A Withdrawn GB2198791A (en) | 1986-08-20 | 1986-08-20 | A geared turbofan gas turbine engine with a booster compressor |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2198791A (en) |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4916894A (en) * | 1989-01-03 | 1990-04-17 | General Electric Company | High bypass turbofan engine having a partially geared fan drive turbine |
| US4947642A (en) * | 1988-04-11 | 1990-08-14 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Propfan turbo-engine |
| GB2230298A (en) * | 1989-01-03 | 1990-10-17 | Gen Electric | Geared counterrotating turbine/fan propulsion system |
| DE4131713A1 (en) * | 1991-09-24 | 1993-04-08 | Mtu Muenchen Gmbh | Booster compressor for turbo-fan engine with high by-pass ratio - is formed as precompressor stage, of core compressor, and connected to it |
| WO2008105815A3 (en) * | 2006-08-22 | 2008-12-04 | Rolls Royce North American Tec | Gas turbine engine with intermediate speed booster |
| EP1939430A3 (en) * | 2006-12-21 | 2010-01-20 | General Electric Company | Turbofan engine assembly and method of assembling same |
| EP2233721A1 (en) * | 2009-03-09 | 2010-09-29 | Rolls-Royce plc | Gas turbine engine |
| WO2014018382A1 (en) | 2012-07-24 | 2014-01-30 | United Technologies Corporation | Geared fan with inner counter rotating compressor |
| DE102014226696A1 (en) * | 2014-12-19 | 2016-06-23 | Rolls-Royce Deutschland Ltd & Co Kg | Pre-compressor device, retrofit kit and aircraft engine |
| WO2016103550A1 (en) * | 2014-12-24 | 2016-06-30 | 川崎重工業株式会社 | Aircraft engine device |
| WO2016103551A1 (en) * | 2014-12-24 | 2016-06-30 | 川崎重工業株式会社 | Aircraft engine device |
| CN114151206A (en) * | 2020-09-07 | 2022-03-08 | 中国航发商用航空发动机有限责任公司 | Fan driving structure and assembling method thereof |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11512637B2 (en) * | 2020-11-12 | 2022-11-29 | General Electric Company | Turbine engine bearing arrangement |
| CN114810348B (en) * | 2021-01-19 | 2024-08-02 | 中国航发商用航空发动机有限责任公司 | Transmission mechanism, turbofan engine and assembly method |
-
1986
- 1986-08-20 GB GB08620199A patent/GB2198791A/en not_active Withdrawn
Cited By (24)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4947642A (en) * | 1988-04-11 | 1990-08-14 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Propfan turbo-engine |
| US4916894A (en) * | 1989-01-03 | 1990-04-17 | General Electric Company | High bypass turbofan engine having a partially geared fan drive turbine |
| GB2230298A (en) * | 1989-01-03 | 1990-10-17 | Gen Electric | Geared counterrotating turbine/fan propulsion system |
| GB2230298B (en) * | 1989-01-03 | 1993-09-22 | Gen Electric | Geared counterrotating turbine/fan propulsion system |
| DE4131713A1 (en) * | 1991-09-24 | 1993-04-08 | Mtu Muenchen Gmbh | Booster compressor for turbo-fan engine with high by-pass ratio - is formed as precompressor stage, of core compressor, and connected to it |
| WO2008105815A3 (en) * | 2006-08-22 | 2008-12-04 | Rolls Royce North American Tec | Gas turbine engine with intermediate speed booster |
| US8209952B2 (en) | 2006-08-22 | 2012-07-03 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine with intermediate speed booster |
| EP1939430A3 (en) * | 2006-12-21 | 2010-01-20 | General Electric Company | Turbofan engine assembly and method of assembling same |
| US7716914B2 (en) | 2006-12-21 | 2010-05-18 | General Electric Company | Turbofan engine assembly and method of assembling same |
| EP2233721A1 (en) * | 2009-03-09 | 2010-09-29 | Rolls-Royce plc | Gas turbine engine |
| US10125694B2 (en) | 2012-07-24 | 2018-11-13 | United Technologies Corporation | Geared fan with inner counter rotating compressor |
| WO2014018382A1 (en) | 2012-07-24 | 2014-01-30 | United Technologies Corporation | Geared fan with inner counter rotating compressor |
| EP2877725B1 (en) * | 2012-07-24 | 2020-05-06 | United Technologies Corporation | Geared fan with inner counter rotating compressor |
| US9228535B2 (en) | 2012-07-24 | 2016-01-05 | United Technologies Corporation | Geared fan with inner counter rotating compressor |
| DE102014226696A1 (en) * | 2014-12-19 | 2016-06-23 | Rolls-Royce Deutschland Ltd & Co Kg | Pre-compressor device, retrofit kit and aircraft engine |
| WO2016103551A1 (en) * | 2014-12-24 | 2016-06-30 | 川崎重工業株式会社 | Aircraft engine device |
| JP2016121565A (en) * | 2014-12-24 | 2016-07-07 | 川崎重工業株式会社 | Engine device for aircraft |
| EP3246546A4 (en) * | 2014-12-24 | 2018-10-24 | Kawasaki Jukogyo Kabushiki Kaisha | Aircraft engine device |
| JP2016121571A (en) * | 2014-12-24 | 2016-07-07 | 川崎重工業株式会社 | Engine device for aircraft |
| US10605165B2 (en) | 2014-12-24 | 2020-03-31 | Kawasaki Jukogyo Kabushiki Kaisha | Aircraft engine apparatus |
| WO2016103550A1 (en) * | 2014-12-24 | 2016-06-30 | 川崎重工業株式会社 | Aircraft engine device |
| US11566566B2 (en) | 2014-12-24 | 2023-01-31 | Kawasaki Jukogyo Kabushiki Kaisha | Aircraft engine power generator disposed inside of a stationary nose cone |
| CN114151206A (en) * | 2020-09-07 | 2022-03-08 | 中国航发商用航空发动机有限责任公司 | Fan driving structure and assembling method thereof |
| CN114151206B (en) * | 2020-09-07 | 2023-11-14 | 中国航发商用航空发动机有限责任公司 | Fan driving structure and assembling method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| GB8620199D0 (en) | 1986-10-01 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |