GB2069613A - Gas turbine aircraft powerplant - Google Patents
Gas turbine aircraft powerplant Download PDFInfo
- Publication number
- GB2069613A GB2069613A GB8005253A GB8005253A GB2069613A GB 2069613 A GB2069613 A GB 2069613A GB 8005253 A GB8005253 A GB 8005253A GB 8005253 A GB8005253 A GB 8005253A GB 2069613 A GB2069613 A GB 2069613A
- Authority
- GB
- United Kingdom
- Prior art keywords
- fan
- powerplant
- turbine
- gas turbine
- engine
- 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
Links
- 239000007789 gas Substances 0.000 abstract description 16
- 230000001141 propulsive effect Effects 0.000 abstract description 5
- 238000002485 combustion reaction Methods 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
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
- F02K3/062—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 aft fan
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
The powerplant comprises a core gas turbine engine 11 and a fan module comprising a fan 12 directly driven from a fan turbine 13 by the core exhaust gases. The axis of the fan module is disposed at an angle ??? to the axis of the core engine of <IMAGE> of the aircraft in which the powerplant is to be installed so as to improve propulsive efficiency. <IMAGE>
Description
SPECIFICATION
Gas turbine powerplant for an aircraft
This invention relates to a gas turbine powerplant for an aircraft.
In recent years, with the escalation in the real cost of the fuel oils used in gas turbine engines, the benefit to be gained by improvement in the propulsive efficiency of the engines has increased considerably, and quite small gains have become worthwhile. Considering the powerplant and its interaction with the aircraft which it powers, it transpires that the best propulsive efficiency can be achieved if the thrust from the powerplant has a small upward component which reduces the aerodynamic lift required from the aircraft wings and hence reduces the induced drag. In order to provide this upward component the efflux from the powerplant should be angled downwardly at the angle whose tangent is the ratio of lift to drag for the aircraft in question.
Unfortunately, tilting the whole engine downwardly to provide this angle of thrust is not effective because the airflow entering the engine is then not parallel with the engine axis, and this leads to a loss in engine efficiency either from the angled entry of the air or from the deflection necessary to direct the air axially into the engine.
We have invented a gas turbine powerplant in which the air entry to the core engine is axial and yet the thrust can be at the desired small downward angle.
According to the present invention a gas turbine powerplant for an aircraft comprises a core gas turbine engine and a fan module comprising a fan directly driven from a coaxial fan turbine, the core exhaust gas passing through the fan turbine to drive the fan, and the axis of the fan module being disposed at an angle to the axis of the core engine which is
lift tan-' drag of the aircraft in which the powerplant is to be installed whereby the thrust from the powerplant is caused to be at this angle to the core engine axis.
The fan turbine is preferably located directly downstream of the core engine, and the fan may then be a mid or rear fan driven from the tips of the blades of at least one stage of the fan turbine.
The invention will now be particularly described, merely by way of example, with reference to the accompanying drawing which is an axial section through a gas turbine powerplant in accordance with the present invention.
In the drawing the powerplant is seen to consist of an outer casing 10 within which are mounted a core gas turbine engine generally indicated at 11, a fan generally indicated at 1 2 and a fan turbine generally indicated at 13, the fan 1 2 and fan turbine 1 3 together making up a fan module.
The core gas turbine engine ii comprises a casing 1 4 within which are carried in flow series a low pressure axial flow compressor 15, a high pressure axial flow compressor 16, a combustion system 17, a high pressure axial flow turbine 1 8 and a low pressure axial flow turbine 19. The high pressure compressor 1 6 and turbine 1 8 are drivingly interconnected by a high pressure shaft 20, while the low pressure compressor 1 5 and turbine 1 9 are similarly drivingly interconnected by a low pressure shaft 37. The rotors of the core are all coaxial.
Operation of the components of the core engine 11 is conventional and will not be described in detail, however, it will be appreciated that overall the operation of the engine is to take air in, compress it in the low and high pressure compressors, burn fuel in the compressed air in the combustion system, and allow the products of combustion to expand through the high and low pressure turbines to drive these turbines and, via the respective shafts, the high and low pressure compressors.
The core engine 11 is designed so that the exhaust gases leaving the low pressure turbine 1 9 have a considerable amount of residual energy. This energy is utilised by directing the exhaust gases into the multi-stage fan turbine 13, which effectively forms a continuation of the high and low pressure turbines 1 8 and 1 9 but whose axis is at an angle to that of the rotors of the core engine 11. The fan turbine 1 3 takes most of the remaining energy from the exhaust gases, and they finally flow through the propulsive nozzle 20, coaxial with the fan turbine 13, to provide some propulsive thrust.
In order to support the turbine 1 3 for rotation, a set of guide vanes 21 are provided between the low pressure turbine 1 9 and the fan turbine. The guide vanes 21 are supported from the rearward extremity of the core engine casing 1 4 and carry a forwardly projecting bearing panel 22 and a rearwardly projecting panel 23. The panel 22 carries a bearing 24 and hence supports the low pressure turbine 19, while the rearward panel 23 carries the bearing 25 which supports the upstream part of the fan turbine 1 3.
Similarly, downstream of the turbine 1 3 a set of vanes 26 extend from the fan turbine casing 27 to support a bearing panel 28 and hence, via a bearing 29, the downstream part of the fan turbine 1 3.
As mentioned above, the fan turbine 1 3 is a multi-stage device and its first rotor stage comprises relatively strong rotor blades 30.
The stage of blades 30 carries at its outer extremity an annular drive coupling 31 through which is driven an annular fan disc 32 and hence the row of fanblades 33 making up the fan 1 2. The disc 32 is carried by the coupling 31 coaxial with the fan turbine 1 3 and thus at an angle to the axis of the rotors of the core engine 11.
It will be seen that the fan blades 33 operate to compressor air flowing in the annular passage between the outer casing 10 of the powerplant and an inner casing which forward of the fan comprises the cord engine casing 14 and rearward of the fan comprises the fan turbine casing 27. That part of the casing 10 downstream of the fan, and the casing 27 together define an annular passage coaxial with the fan 12 and fan turbine 1 3 and terminating in an annular propulsion nozzle 34 again coaxial with the fan and fan turbine. In order to support the fan turbine casing 27 a row of struts 35 extend across the annular passage from the casing 10 to the casing 27.
The fan 12, fan turbine 1 3 and associated casings can therefore be considered to be a 'fan module which is to some degree independent of the core engine 11. In particular the fan module may be angled to the axis of the core engine, as described above. The angle of the fan module axis, and hence of the thrust producing flow of gas from the engine, to the axis of the core engine is 8".
This angle can easily be arranged to be that angle whose tangent is the ratio of the lift to the drag of the aircraft which is to be powered by the powerplant, i.e.
lift 8 = tan drag
Normally the angle 8 will be quite small, of the order of 5 , and the fan module can easily be canted at such an angle.
The fan 12 of the embodiment described is of a type termed a 'mid fan' in the art, because the fan lies in the mid-region of the axial extent of the powerplant. It will be seen that it would be quite possible to move the fan rearwardly so that it becomes an 'aft fan'; in this case it may be advantageous to use a short cowling in place of the long outer cowling 10.
Claims (6)
1 A gas turbine powerplant for an aircraft comprising a core gas turbine engine and a fan module comprising a fan directly driven from a coaxial fan turbine, the core exhaust gas passing through the fan turbine to drive the fan, and the axis of the fan module being disposed at an angle to the axis of the core engine which is
lift tan- ' drag of the aircraft in which the powerplant is to be installed whereby the thrust from the powerplant is caused to be at this angle to the core engine axis.
2. A gas turbine powerplant as claimed in claim 1 and in which the fan turbine is located directly downstream of the core engine.
3. A gas turbine powerplant as claimed in claim 2 and in which the fan is driven from the tips of the blades of at least one stage of.
the fan turbine.
4. A gas turbine powerplant as claimed in claim 3 and comprising a mid fan.
5. A gas turbine powerplant as claimed in claim 3 and comprising an aft fan.
6. A gas turbine powerplant substantially as hereinbefore particularly described with reference to the accompanying drawing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8005253A GB2069613B (en) | 1980-02-15 | 1980-02-15 | Gas turbine aircraft powerplant |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8005253A GB2069613B (en) | 1980-02-15 | 1980-02-15 | Gas turbine aircraft powerplant |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| GB2069613A true GB2069613A (en) | 1981-08-26 |
| GB2069613B GB2069613B (en) | 1983-07-13 |
Family
ID=10511408
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8005253A Expired GB2069613B (en) | 1980-02-15 | 1980-02-15 | Gas turbine aircraft powerplant |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2069613B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4129357A1 (en) * | 1991-07-03 | 1992-08-27 | Kastens Karl | Method of increasing power of aircraft jet engine - involves installing additional fan in rear part of engine |
| USD1099054S1 (en) * | 2023-09-27 | 2025-10-21 | Acer Incorporated | Heat dissipation module |
-
1980
- 1980-02-15 GB GB8005253A patent/GB2069613B/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4129357A1 (en) * | 1991-07-03 | 1992-08-27 | Kastens Karl | Method of increasing power of aircraft jet engine - involves installing additional fan in rear part of engine |
| USD1099054S1 (en) * | 2023-09-27 | 2025-10-21 | Acer Incorporated | Heat dissipation module |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2069613B (en) | 1983-07-13 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PCNP | Patent ceased through non-payment of renewal fee |