DE3600852A1 - TURBO PROPELLER GAS TURBINE PLANE ENGINE - Google Patents

Description

The discovery decides on gas turbine aircraft engines the door propeller type, commonly known as "Turbcprcps" are designated.

These engines usually have an engine nacelle, one or more compressors, one Combustion device, a compressor that drives the turbines and one or more propellers, which are driven by a turbine via a reduction gear. The propeller (s) can be from a low pressure turbine or a free power turbine are driven, the downstream of the low pressure turbine is arranged. These engines also have an accessory gearbox that is driven by a turbine is driven to provide a drive for fuel pumps, for lubricant pumps and other accessories to i ie ^ ern.

Turboprops of the type in which the propeller or propellers are located at the downstream end of the gas turbine engine are called thrust turbo-props. Thrust turbo-props can be problematic in that airflow Using the engine nacelle upstream of the propeller or propellers, pressurize or cause eddies generated the shape of the engine nacelle, and this reduces the efficiency of the propeller or the Propeller."

The invention is therefore based on the object of providing a door boprop gas turbine aircraft engine of the thrust type create what flow disturbances in the form of Suction points and eddies in the

nacelle after the propeller air flowing is reduced.

The invention is based on a turboprop gas turbine aircraft engine the thrust design, which comprises the following components one behind the other in the direction of flow:

A compressor, a combustion device, a turbine driving the compressor, a propeller drive turbine and at least one propeller driven by the propeller drive turbine via a reduction gear is driven. The engine upstream of the propeller is from an engine nacelle and a nose cone is positioned upstream of and defines the compressor an annular inlet together with the upstream wärtigen End of the engine nacelle. The reduction gear is located downstream of the propeller drive turbine and upstream of the propeller, wherein the compressor, the compressor drive turbine, the propeller drive turbine, the reduction gear and the propeller are arranged coaxially. With such an engine the object is achieved in that an accessory gear housing within the nose cone arranged upstream of the compressor and driven by a turbine, and that the accessory gearbox is arranged so that an axially symmetrical, aerodynamically designed engine nacelle upstream of the propeller is formed to generate suction and To reduce eddies in the air flowing out of the engine nacelle after the propeller.

The compressor may include a low pressure compressor and a high pressure compressor, and the Compressor drive turbine includes a low pressure turbine that drives the low pressure compressor and a high pressure turbine drives the high pressure compressor.

The propeller drive turbine can be the low pressure turbine or a power turbine which is arranged downstream of the low-pressure turbine and is driven by their exhaust gases.

The accessory gearbox can be driven by the low pressure turbine, the high pressure turbine, or a power turbine will .

The engine nacelle may have an annular exhaust outlet upstream of the propeller.

The engine nacelle can have a radially extending strut upstream of the propeller, the one has inner exhaust duct which has one or more outlets in the strut to transfer the exhaust gases downstream to straighten the surface of the strut.

The propeller has a propeller hub cap an axially extending inner duct to direct the exhaust gases to an annular outlet downstream of the propeller

The reduction gear can be a planetary gear.

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The engine can have two propellers rotating in opposite directions, and the propeller or propellers can be of the Be grafted.

Embodiments of the invention are shown below described with reference to the drawing. In the drawing show:

Fig. 1 is a broken away view of a turbo " propeller gas turbine aircraft engine of the Push type according to the invention;

Fig. 2 is a broken away view of a modified one Embodiment of a turbo-propeller gas turbine aircraft engine the push type according to the invention;

3 is a broken away view of a third embodiment of a turbo propeller gas turbine aircraft engine the push type according to the invention;

Fig. 4 is a broken away view of a fourth embodiment of a turbo-propeller gas turbine aircraft engine the push type according to the invention;

5 shows a sectional view on a larger scale

the sealing arrangement between the engine nacelle and the propeller hub cap at the management form according to FIG. 4;

Fig. 6 is a broken away view of another embodiment of a turbo-propeller gas turbine aircraft engine the push type according to the invention.

Referring to Fig. 1, a turbo-propeller gas turbine aircraft engine is included 10 of the Schaubbauart a gas generator 11, one behind the other in the direction of flow Low pressure compressor 20, a high pressure compressor 22, a combustion device 24, a high pressure turbine 26, a low pressure turbine 28 and an annular outlet 18. The gas generator 11 is of one Enclosed engine nacelle 12 and a nose cone 14 is upstream of the low pressure compressor 20 and forms an annular inlet 16 to the upstream end of the engine nacelle 16. The low pressure compressor 20 and the high pressure compressor 22 compresses that entering the gas turbine engine 10 via inlet 16 Air. The compressed air is then fed to the incinerator 24 where fuel is burned, to generate hot gases. The hot gases flow through the high pressure turbine 26 or the low pressure turbine 28 and drive them on. The turbines in turn drive the high-pressure compressor 22 or the low-pressure compressor 20 via coaxial shafts 30 and 32, respectively.

A propeller 50 provided with a plurality of blades is located downstream of the gas generator 11 and coaxial thereto. The propeller 50 is aerodynamically designed

Propeller hub cap 52 equipped. The multi-shovel Propeller 50 is driven by a turbine via a reduction gear 36, namely at this embodiment from the low-pressure turbine 28. The reduction gear 36 is coaxial with the propeller 50 and the gas generator 11 and axially between the low pressure turbine 28 and the propeller 50.

A gear box 34 for accessory devices drives auxiliary devices such as fuel pumps, Oil pumps and so on, and this accessory gear is upstream of the low pressure compressor 20 within of the nose cone 14. The accessory gear 34 is driven by a turbine, in this case Exemplary embodiment through the low-pressure turbine 28 across the world 32.

In that the reduction gear 36 is arranged coaxially with the gas generator 11 and with the propeller 50 and is axially between the low pressure turbine 28 and the propeller 50, and in that the accessory gearbox 34 is housed upstream of the low-pressure compressor 20 within the nose cone 14, can the engine nacelle 12 with a relatively small diameter axially symmetrically and aerodynamically upstream of the propeller 50 are designed so that suction points and eddy formations in the air flow that over the Engine nacelle 12 after the propeller 50 flows off, can be reduced. By reducing the suction

put and the disturbances of the air flow that flows after the propeller 50, the efficiency of the propeller 50 increased.

Known turbo-propeller gas turbine aircraft engines generated suction points and disturbances in the air flow, which over the engine nacelle after the Propeller drained. These disturbances have decreased the efficiency of the propeller and they have become caused by the fact that the engine nacelle was not designed symmetrically and not aerodynamically. The main reason for this so far has been the fact that the accessory gearbox is outside the compressor housing arranged and driven by a radially extending shaft from the main drive shaft.

Fig. 2 shows a turbo-propeller gas turbine aircraft engine 10 of the thrust type, which is similar to the engine of FIG. The gas generator 11 is according to that Fig. 1 is identical and the same parts are provided with the same reference numerals. One with multiple shovels provided propeller 50 is downstream and coaxial with the gas generator 11, and the propeller 50 is with an aerodynamically designed propeller hub cap 52 is provided. The one provided with several shovels Propeller 50 is powered by a power turbine via a shaft 42 and a reduction gear driven. The power turbine 40 is downstream of the low-pressure turbine 28, and the exhaust gases from the gas generator 11 drive the power turbine 40.

The reduction gear 36, the shaft 42 and the power turbine 40 as well as the propeller 50 are axially to the gas generator 11. The reduction gear 36 is axially between the low pressure turbine 28 and the propeller 50.

The accessory gear case 40 is upstream of the low pressure compressor 20 within the nose cone 14 and is driven by the low-pressure turbine 28 via a shaft 32.

The engine nacelle 12 again has a relatively small diameter and is upstream of the propeller Axially symmetrical and aerodynamically designed, so that disturbances of the air flow over the engine nacelle 12 after the propeller 50 can be reduced.

Fig. 3 shows a turbo-propeller gas turbine aircraft engine 10 of the thrust type, which corresponds to the engine of FIG. The gas generator 11 is identical that of FIG. 1 and the same parts are provided with the same reference numerals. Two rotating in opposite directions multi-bladed propellers 70, 72 of the plug type, i.e. thin section and tall Arrow shape to delay the shock wave formation with the possibility of high power application work, are arranged downstream of the gas generator 11 and coaxially to this, and the propellers 70,72 are provided with aerodynamically designed hub caps 74. The propellers 70 driven in the opposite direction, 72 are driven by the low-pressure turbine 28 via the

Reduction gear 36 driven- The reduction gear 36 is coaxial with the propellers 70, 72 and the gas generator 11 and axially between the low pressure turbine 28 and the propellers 70,

The accessory gearbox 34 is upstream of the low pressure compressor 20 within the nose cone 14 and is driven by the low pressure turbine 28 via the shaft 32.

The engine nacelle 12 has a relatively small diameter and it is upstream of that in the opposite direction rotating propellers 70, 72 designed aerodynamically and axially symmetrical, so that disturbances and vortex formation the air flow flowing over the engine nacelle 12 to the propellers 70, 72 is reduced will.

In this embodiment, the gas generator not an annular outlet 18, but a strut 60 upstream of the propellers 70, 72 and downstream the low-pressure turbine 28 arranged, which protrudes radially from the engine nacelle 12 and part of the Can form structure that holds the engine on the aircraft. The strut 60 has an inner channel 62, through which the exhaust gases from the gas generator 11 flow. The exhaust gases flow to a nozzle 64 which is used can to direct the exhaust gases downstream via the tail of the aircraft, as detailed in the published British patent application GB 21 38 507A

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is described. The strut 60 may be provided with outlets generally slotted and vanes be to expel the exhaust gases in the downstream direction via the strut and suction points created by the Strut 60 are generated to suppress.

The engine nacelle 12 has a relatively small diameter and is upstream of the counter-rotating Propellers 70, 72 axially symmetric and aerodynamic designed so that flow disturbances flowing over the engine nacelle 12 after the propellers Air.

Fig. 4 shows a turbo-propeller gas turbine aircraft engine 10 of the push type, which corresponds to that of FIG. The gas generator 11 is identical to that 1 and the same parts are provided with the same reference numerals. The propeller 80 is upstream of the Gas generator 11 is coaxial with this and the propeller 80 is provided with an aerodynamic hub cap 82. The propeller 80 is driven by the low pressure turbine 28 via a reduction gear 36 which is coaxial to the propeller 80 and to the gas generator 11 and axially between the low-pressure turbine 28 and the propeller The accessory gearbox 34 is upstream of the low pressure compressor 20 within the nose cone 14 and is driven by the low pressure turbine 28.

The hub cap 82 is provided with an inner annular channel 88 which runs axially and the exhaust gases from the gas generator 11 between the blade roots 90 of the propeller 80 downstream of an annular outlet 86 in the hub cap 82

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of the propeller 80 transferred. The annular channel 80 accordingly directs the exhaust gases from the propeller blades path. Between the upstream end of the hub cap 82 and the downstream end of the Engine nacelle 12, a seal 84 is provided, which is shown on a larger scale in FIG. The upstream end 94 of the hub cap 82 projects axially above the downstream end 92 of the engine nacelle 12 in front and is radially distanced therefrom. A plurality of annular ribs 96 extend radially from the upstream end 94 of the hub cap 82 to the downstream end 92 of the engine nacelle 12 or vice versa to create a labyrinthine seal.

Fig. 6 shows a turbo-propeller gas turbine aircraft engine 10 of the push type, which corresponds to that of FIG. The gas generator is identical to that after 4 and the same parts are provided with the same reference numerals. The propeller 80 is downstream of the gas generator 11 and coaxial therewith. The propeller 80 is provided with a hub cap 82. The propeller 80 is powered by a power turbine 40 via a shaft 42 and a reduction gear driven. The power turbine 40 is downstream of the low-pressure turbine 28. The power turbine 40, the shaft 42 and the reduction gear 36 are coaxial with the gas generator 11 and the propeller 80. The accessory gear 34 is in turn located upstream of the low-pressure compressor 20 within the hub cone and is through the power turbine 40 via a

Driven shaft 44, which is coaxial with shafts 30, 32, 42.

The reduction gear can in all exemplary embodiments from expediently as a planet be designed wheel drive.

Claims (1)

Patent attorneys D i ρ i.-1 r. G. C u rt Wallach ■ ' European patent agent Di pi.-1 η g. Q ü nther Koch;. European Patent Attorneys 3600852 Dipl.-Phys. Dr Tino Haibach * Dipl.-Ing. Rainer Feldkamp D-8000 Munich 2 · Kaufingerstraße 8 ■ Telephone (0 89) 2 60 80 78 · Telex 5 29 513 wakai d Date January 14, 1986 London SW1E 6AT
England Turbopropeller gas turbine aircraft engine
Patent claims: Turbopropeller gas turbine aircraft engine with pneumatic screw, with a low-pressure compressor, a high-pressure compressor, a combustion device of a high-pressure turbine that drives the high-pressure compressor, with a low-pressure turbine that drives the low-pressure compressor \, with a propeller drive turbine, \ which drives at least one pusher propeller via a reduction gear, the Gas turbine engine upstream of the pusher propeller is enclosed by an engine nacelle, which upstream of the low-pressure compressor a bullet-shaped Has nose having a ring inlet together with the upstream end of the Engine nacelle forms, and where the low-pressure compressor, the high-pressure compressor, the High pressure turbine, the low pressure turbine, the propeller drive turbine, the reduction gear and the pusher propeller and the reduction gear are arranged coaxially downstream of the propeller drive turbine and is upstream of the pusher propeller, characterized in that an accessory gear box (34) in the nose cone (14) upstream of the low-pressure compressor (20) arranged and driven by the Niedsrdruckturbine (28), and that the reduction gear (36) and the accessory gear box (34) are arranged in such a way that they are axially symmetrical aerodynamically designed engine nacelle (12) upstream of the pusher propeller (50) form to reduce the creation of suction and eddies in the air flow passing over the Engine nacelle (12) after the pressure propeller (50) flows. . Turboprope 1-series gas turbine engine according to claim 1, characterized in that the propeller drive turbine is a low pressure turbine (28). 3. Turbopropeller gas turbine aircraft engine according to claim 1, characterized in that the propeller drive turbine is a power turbine (40), which are arranged downstream of the low-pressure turbine (28) and is driven by their exhaust gases. 4. Turbopropellar gas turbine jet engine according to claim 1, characterized in that the engine nacelle (12) an annular gas α us let (18) upstream of the pressure propeller (50). 5. Turbopropeller gas turbine aircraft engine according to claim 1, characterized in that the engine nacelle (12) has a radially extending strut (60) upstream of the pusher propeller (70, 74), and that the strut (60) has an inner Has exhaust gas duct (62) having one or more outlets (66) in the strut (60) to directing the exhaust gases in a downstream direction across the surface of the strut (60). 6. Turbopropel single gas turbine aircraft engine according to claim 1, characterized in that the pusher propeller (80) has a propeller hub cap (82), which has an axially extending inner channel (88) to the exhaust gases to an annular outlet (86) downstream of the pusher propeller (80). 7. Turbopropeller gas turbine aircraft engine according to claim 1, characterized in that the reduction gear (36) is a planetary gear reduction gear is. 8. Turbopropeller gas turbine aircraft engine according to claim 1, characterized in that the engine has two pusher propellers (70, 74) running in the opposite direction having. 9. Turboprop gas turbine engine according to claim 1, characterized in that the propeller or the propeller «/ on the Propfän-Bauart are.