CN105882956A - Modularized power equipment and air vehicle with lifting rotor wing - Google Patents

Abstract

Modularized power equipment (10) is provided with a main speed changing box (20), a turbine engine (40) and a heat exchanger (60). The main speed changing box comprises a basically vertical rotor wing mast (21) and comprises at least one rotary speed reducing gear and a table rack (23) which are arranged in a flat hood (22); the turbine engine is provided with an engine shell (42), an output shaft (41) stretches out of the shell, is inserted into the flat hood and is basically parallel to the rotor wing mast (21), and the engine shell is deviated from the table rack (23) and does not make contact with the table rack (23) in the longitudinal direction; the heat exchanger (60) longitudinally extends behind the turbine engine, and on the contrary, the rotor wing mast is longitudinally arranged in front of the turbine engine. The invention further relates to an air vehicle with a lifting rotor wing, and the air vehicle comprises the modularized power equipment.

Description

Modular power equipment and be provided with the aircraft of lifting rotor

Technical field

The present invention relates to a kind of modular power equipment, further relate to a kind of aircraft being provided with lifting rotor, This aircraft is driven by power-equipment and rotates.

The power-equipment of this aircraft generally includes the turbogenerator driving main-gear box.

Turbogenerator generally includes the gas turbine having gas generator, gas generator driving work whirlpool Wheel rotates.Work turbine can be independently of what is called " freely " turbine of gas generator.This gas generator It is generally of at least one and supplies compressed-air actuated compression stage for combustor.

Main-gear box includes rotor mast, is used for driving lifting rotor to rotate.Additionally, this main-gear box is permissible Including a delivery outlet to drive rotor, such as, the rotor of the yawing rotation controlling described aircraft is driven.

Attachment means and angle transmission launching apparatus subsequently it may be possible to be placed in work turbine and main-gear box it Between.Such as, this attachment means includes the parts of the angular displacement between two rotary shafts of regulation.

A kind of turbogenerator is generally horizontally set in support platform.In other words, turbogenerator Output shaft be horizontal.On the contrary, the main-gear box that support platform is carried is in substantially vertical On position, rotor mast is driven by substantially vertical main-gear box and rotates.

Older generation's turbogenerator generally there are the sizable problem of weight and volume, and this makes them be difficult to install. More specifically, such older generation's turbogenerator is it is possible that of a relatively high fuel oil consumption.

But, the turbogenerator in some modern times is relative compact.This turbogenerator is known include single Compression stage and combustor, it is that " inversion type " and the overall dimensions making turbogenerator can be big that combustor is stated to be Big fall is little.For convenience's sake, and in order to easily identify it, such turbogenerator is claimed For " close-coupled turbogenerator ".

In order to improve the performance of close-coupled turbogenerator, particularly its fuel consumption, power-equipment can wrap Include heat exchanger.Although turbogenerator is strictly close-coupled, but heat exchanger is found to be heaviness on the contrary 's.For example, by using the hot gas obtained from the delivery outlet of turbogenerator, heat exchanger is used for Preheating air between delivery outlet and the combustor of turbogenerator of the compression stage of turbogenerator.

Then, this heat exchanger is secured to heating fresh air on turbogenerator, meanwhile, and fresh sky Gas is compressed by gas generator before entering into the combustion chamber.

Therefore, fresh air is inhaled into turbogenerator, then experiences each compression stage and compresses.Pressed The fresh air of contracting is directed in heat exchanger, with heated before arriving combustor.In this situation Under, compressed air and fuel one combust, thus produce hot gas, it is through at least one turbine Expand.Turbogenerator thus can include is connected to the turbine of multiple grades of described compressor and includes freedom Work turbine, these turbines are rotated by described hot gas.Then, hot gas is collected by heat exchanger, With before hot gas is discharged into air, heat the fresh air of entrained vortex turbine.

Show as relatively low fuel oil to consume by contrast, including close-coupled turbogenerator and heat exchanger with it Assembly be found subsequently compared with traditional electromotor, volume is heavy.

But, arrange that such assembly is not obvious.

Heat exchanger is in place may result in increase aircraft skin width and/or height and/or length.So After, the surface area that aircraft is total, particularly its front surface area add compared with routine setting.This can lead The aerodynamic towing causing aircraft increases.

Arrange connect that the close-coupled turbogenerator of heat exchanger can result in aircraft center of gravity position notable Changing, such as, the wing of aircraft may be caused adverse effect by this.Particularly, in order to ensure aircraft Static stability, vertically and horizontally regulator then it is thus desirable to aircraft formulate specific dimensions.

Background technology

Document EP 1216190 describes a kind of integrated engine and main-gear box.

Turbogenerator is arranged in shell, and main-gear box is combined in shell and is connected to this turbine.Main transformer Speed case is installed in cover, and cover and shell are mutually integrated to constitute independent unit.

This turbogenerator has the horizontal output shaft for driving main-gear box.

Document FR 2956700 describes a kind of whirlpool with the most substantially vertical output shaft Turbine, this output shaft is kept by single bearing.

Document US 5226350 describes a kind of aircraft, has the ring around two mutually despun rotors. One electromotor rotates with the propeller hub of the driving mutually despun rotor of carrying in being disposed in ring.This electromotor leads to Cross a major axis and be connected to propeller hub, this major axis be allowed between propeller hub and electromotor axial, tilt and/or flat Line misregistration.

Document US 5108043 describes a kind of helicopter power-equipment with two electromotors.Each start Machine drives main-gear box by power transmission shaft, and power transmission shaft one end has groove, other end carrier gear.

Document EP 0760777 describes one and has the main-gear box of planet (turnover) gear train.Electromotor Main-gear box can also be connected to by bevel gearing.

Document DE 20006526 describes a kind of axle being driven rotor by belt dressing.

Therefore, these documents do not provide about the teaching arranging the power-equipment including main-gear box, and this is main Change speed gear box is driven by the close-coupled turbogenerator cooperated with heat exchanger and rotates.

Known also have following documents: US 2005/115770 A1, US 5823470 A, US 5054716 A, GB940024 A, US 2011/121127 A1 and FR 2905983 A1.

Document US 2005/115770 A1 suggested a kind of device tilt with change speed gear box.

Document US 5823470 A describes a kind of aircraft with two tilting rotors.

Document US5054716 A also illustrates a kind of deflected-thrust vehicle with turbogenerator, whirlpool Turbine coordinates with the main-gear box with mast.

Summary of the invention

Therefore, the purpose of the present invention is to propose to such power-equipment.

According to the present invention, power-equipment is provided with main-gear box and turbogenerator, and main-gear box has the most vertical Straight rotor mast, described mast is suitable for the propeller hub of rotary wing, and turbogenerator has output shaft to drive Dynamic described main-gear box, this power-equipment has the heat exchanger being fixed on this turbogenerator.

This power-equipment has a following significance:

Main-gear box has at least one rotational delay level being arranged in flat cover and stands upright on flat cover Stand on end face, rotor mast passes described stand；

Described turbogenerator includes that engine housing, output shaft stretch out in engine housing, when outside electromotor Shell is arranged in time on the end face of flat cover in the flat cover of output shaft insertion, and output shaft is basically parallel to rotor mast, Engine housing relative to stand deviation and does not contacts with stand in the vertical；And

Heat exchanger is at the rear longitudinal extension of turbogenerator, and rotor mast is placed longitudinally in contrary direction On be positioned at the front of turbogenerator.

This power-equipment is not tilting gearing.Owing to stand keeps static relative to flat cover, so, turbine Electromotor is prevented from relative to flat cover motion, and power-equipment is static relative to support platform.

In other words, relative to power-equipment and/or to be provided with the vehicles of this power-equipment vertical vertical To direction, turbogenerator is disposed between rotor mast and heat exchanger.Power is laterally observed in side The observer of equipment is it is observed that this feature.

By being arranged in before and after the symmetry of power-equipment and the vehicles in plane, heat exchanger can be smart Really it is positioned in a lengthwise position.

In a modification, by being placed in a clinoplain, heat exchanger can be arranged tiltably, This clinoplain is extending certain altitude relative to anterior-posterior plane and vertical is being angled up.This angle then may be used See during to be observed power-equipment by observer along short transverse.

Why flat cover is said to be the size being because in its short transverse of " flat " is significantly less than longitudinal direction Size transversely.

Such as, the size in its short transverse is about 150 millimeters (mm), and its lateral dimension is about The order of magnitude of 500mm, so that bull wheel can be put into wherein, its longitudinal size is about the order of magnitude of 1 meter, So that put into gear train.The size that stand presents is height and the about 300mm of about 400mm Diameter.These numerical value are all to be given in an illustrative manner, especially for the flat feature that flat cover is described.

This power-equipment proposes the device with two modules, and before secured together, they are independent , i.e. main-gear box and turbogenerator, electromotor be close-coupled turbogenerator be favourable.Therefore, The two module is different, and exists in two different shells.

Therefore, turbogenerator is all independent, from becoming a set of with main-gear box.Such as, propeller for turboprop Machine and main-gear box are all by competent department's certification independent of one another.

The mechanical connection using vertical output axle makes the two module be mechanically coupled together.

Therefore, this turbogenerator can in the case of not affecting main-gear box from the vehicles removal, Vice versa.Operator replaces out of order propeller for turboprop with another turbogenerator with can not having difficulty Machine.

By the output shaft extended perpendicularly out in engine housing, turbogenerator is mechanically connected to main transformer speed Case.This characteristic gives the use motility that output shaft is certain, and it can allow turbogenerator and main transformer speed A certain degree of dislocation between case.

Additionally, since the output shaft of turbogenerator is directly inserted in main-gear box, this power-equipment is the most not The attachment means being arranged between turbogenerator and main-gear box or angle is needed to drive launching apparatus.

This power-equipment also allows for the aerodynamic quality avoiding reducing aircraft excessively.

It should be pointed out that, that installing the turbogenerator being associated with heat exchanger can have the front table at aircraft The impact in region, face.

But, it being different from conventional configuration, turbogenerator is arranged in substantially by the power-equipment suggestion of the present invention Upper vertical position.

In this case, heat exchanger can on the position of basic horizontal longitudinal extension, with propeller for turboprop Machine aligning in the size range of conventional eyelid covering, therefore, it can take up generally by power-equipment institute The space occupied.

When power-equipment is arranged on board the aircraft, due to turbogenerator aligning, heat exchanger is then Impact on the anterior face area of aircraft is the least.

Additionally, due to be associated with heat exchanger at turbogenerator, turbogenerator can be close-coupled whirlpool Turbine, and be therefore undersized.Thus, the vertically extending height of turbogenerator is rational. Additionally, because output shaft is directly bonded on main-gear box, this main-gear box can include flat cover, this Be conducive to optimizing the height of power-equipment.

Additionally, the distance of turbogenerator longitudinal extension is the shortest, thus reduce heat exchanger to greatest extent Impact on aircraft balance.The distance extended in the vertical including the assembly of turbogenerator and heat exchanger Minimize by being arranged vertically turbogenerator.Therefore, unlike those are to aircraft vertical and horizontal stable The influential scheme of utensil, this layout has active influence to the position of centre of gravity of aircraft.Send out including turbine The lever arm of the assembly of motivation and heat exchanger trends towards diminishing relative to rotor mast, so that aircraft Center of gravity is closer to the rotation axis of rotor.

Therefore, the synergism of these parts of this power-equipment allows to obtain one and can present many The power-equipment of unexpected advantage.

This motive equipment can include one or more following features.

Thus, power-equipment can include the thermal insulation board being arranged between engine housing and described stand.Send out Motivation shell and stand are spaced to each other, so that thermal insulation board may be inserted between them.

Thermal insulation board can include multiple panel, for inserting main-gear box and turbogenerator in more usually mode Between.In this case, such as, thermal insulation board can be provided with and be positioned at turbogenerator and main-gear box Vertical panel between stand, and particularly it is inserted in the horizontal panel between turbogenerator and flat cover.

Additionally, flat cover is optional from the front waist section of carrying stand to the rear section of carrying turbogenerator longitudinally Extend.This characteristic makes engine housing separate with stand well especially.

Additionally, flat cover then can accommodate the power reduction level with bull wheel.Such as, such bull wheel presents Firm, more less expensive than epicyclic train advantage.

Such as, then output shaft directly can engage with bull wheel, or indirectly nibbles via overriding clutch or " flywheel " Close.In the case of turbogenerator surprisingly blocks, such flywheel presents permission lifting rotor with voluntarily Rotate and rotate advantage.

This power-equipment can include the groove bindiny mechanism being arranged between output shaft and main-gear box.

Such groove bindiny mechanism such as can include the groove extremity piece being fixed to described output shaft.

In an embodiment, groove extremity piece engagement bull wheel, it is also sometimes referred to as " there is the actuating device of gear wheel ". Bull wheel is circular gear, thus presents big speed reducing ratio.

In contrast, in another embodiment, the flywheel of groove extremity piece engagement main-gear box, flywheel engages Rotational delay level.Then, such as, the engageable bull wheel of flywheel.

Additionally, this turbogenerator can include the gas turbine with gas generator and be fixed to working shaft Work turbine.

Working shaft and output shaft can overlap, to form a single axle.

But, working shaft and output shaft can be different.In this case, working shaft is the most basic On be parallel to rotor mast, thus be parallel to output shaft.

Parallel to each other by rotor mast, output shaft and working shaft, this power-equipment need not for by them The angle linked together drives launching apparatus.

Therefore, turbogenerator selectively includes reducer gear, and it is positioned at work in engine housing Between axle and output shaft.It is understood that engine housing then can have the what is called " whirlpool around gas turbine Wheel housing " shell and the shell of what is called " reducer shell " around decelerator.Turbine shroud and reducing gearbox Body is fixed to one another to together.Therefore, turbogenerator is modular, and has " gas turbine " module and " subtract Speed device " module.

In this case, such as, the rotary speed of working shaft can 10,000 rev/min (rpm) extremely In the range of 50,000 turns, and the rotary speed of output shaft is lowered to 6,000rpm to 9, the scope of 000 turn In.Then, such as, the actuating device of main-gear box can reduce rotary speed, to reach in rotor mast Rotating speed to about 400rpm.

Additionally, this power-equipment can include attachment means, for engine housing being fixed to flat cover, This attachment means includes bolt ring and multiple centring pin.This attachment means, with the help of directing pin, can make whirlpool Turbine is directed into suitable position；With the help of bolt ring, turbogenerator can be made to be fixed to On main-gear box.

Thermal insulation board can be arranged on the composition surface between turbogenerator and main-gear box.

Additionally, described output shaft can be more than 10 centimetres (cm) from the height that described engine housing stretches out.

Output shaft then has the length of enough motilities.Then, when turbine is installed on main-gear box, Such output shaft can allow the existence of angular deformation.

Turbogenerator needs relatively accurate, to avoid result in fault relative to the location of main-gear box.The biggest Dislocation may result on the parts of main-gear box, act on big power, cause the risk of premature abrasion.

The existence " growing " output shaft is supplied to the amplitude adjustment amount that operator is certain.Additionally, the existence of directing pin Be conducive to being properly positioned of turbogenerator.

Additionally, this power-equipment can have the first lubricating system for lubricating main-gear box and for lubricating whirlpool Second lubricating system of turbine.

The modular construction of this power-equipment allows special lubricating system to be installed in place.

Therefore, the first lubricating system selectively includes mineral oil, and it presents good engaging pressure tolerance Property, the second lubricating system of described turbogenerator can include artificial oil, and it presents low viscosity with good High-temperature capability.

Turbogenerator can include dynamic seal part, and kinetics is with by internal for turbogenerator and its outside Medium separates, and output shaft passes dynamic seal part.Therefore, dynamic seal part is intended to such as avoid lubrication The leakage of fluid.

Additionally, stand selectively includes suspension arrangement, for main-gear box is hanging to support platform. This suspension arrangement can include the oblique suspension rod from stage suspension to platform.

This flat cover can also include a suspension arrangement so that it is can hang relative to platform.

Present invention also offers the aircraft being provided with lifting rotor, lifting rotor includes propeller hub and multiple blade. This aircraft includes the power-equipment of the above-mentioned type.

In this case, described aircraft can include the support platform carrying described power-equipment, described dynamic Power equipment is static relative to described support platform.

Therefore, this power-equipment be not such as document US 2005/115770 A1, US 5823470 A or Tilt component described in US5054716 A.

Accompanying drawing explanation

Referring to the drawings in the following description to embodiment, the present invention and advantage thereof can be understood in more detail, its In:

Fig. 1 is the block diagram of the aircraft of the present invention；

Fig. 2 is the view of the main-gear box of the present invention；

Fig. 3 and Fig. 4 is the view of the turbogenerator being connected to heat exchanger；

Fig. 5 is the view of power-equipment；And

Fig. 6 shows the sectional view of the output shaft engaged with main-gear box.

Detailed description of the invention

The element occurred in more than one accompanying drawing gives identical reference in each accompanying drawing.

Three mutually orthogonal direction X, Y and Z illustrate in some drawings.

First direction X is referred to as " longitudinally ".

Second direction Y is referred to as " laterally ".

Finally, third direction Z is referred to as " in height ".Term " in height " relates to being parallel to the 3rd Any direction of direction Z.

Fig. 1 shows the aircraft 1 with the power-equipment driving rotor 2.In order to avoid Fig. 1 is the most complicated, Other parts of aircraft 1 are shown without.

This rotor 2 has the propeller hub 3 carrying multiple blades 4.It addition, rotor 2 such as includes one group of panel 5 for periodically and/or be commonly controlled the pitch of paddle blade 4.

In order to rotate rotor 2, aircraft has the power-equipment 10 carried by a support platform 6.

This power-equipment 10 has the turbogenerator 40 being connected to heat exchanger.This heat exchanger is used for heating The air compressed by the gas generator of turbogenerator, the most just allows air into combustor.

Then, described turbogenerator drives the rotation of main-gear box 20, and main-gear box 20 has and carries The rotor mast 21 of propeller hub 3.

To this end, main-gear box 20 is provided with at least one rotational delay level 25, for about 400rpm's Rotor mast 21 is driven under speed.Each rotary decelerator level 25 includes being arranged in a flat cover 22 Gear.

With reference to Fig. 2, flat cover in height " extends to end face 24 ', in the vertical from front waist section from bottom surface 24 22 ' extend to rear section 22 ".Flat cover in height be smaller in size than its size in machine and transverse direction. Here it is why this cover is referred to as the reason that " flat " covers.

Rotor mast 21 also extends through the stand 23 on the end face 24 ' being anchored on flat cover 22.Then, rotor mast Bar 21 extends in the height direction, and when the aircraft on the ground, it orients substantially along gravity direction.

Seeing Fig. 1, turbogenerator 40 has the gas turbine 50 being arranged in engine housing 42.

Turbogenerator 40 also has the output shaft 41 being driven rotation by gas turbine 50.This output shaft is from sending out Motivation shell 42 stretches out, preferably stretches out height more than 10 centimetres.

Then, during output shaft 41 is inserted into flat cover.Then, engine housing is fastened to the end face of flat cover 24′.Such as, this power-equipment has attachment means, including bolt ring 90 and multiple centring pin 91, its In Figure 5 seen in detail in.

This centring pin is used for being properly positioned engine housing relative to flat shell.

With reference to Fig. 1, output shaft 41 is then parallel to rotor mast 21.But, output shaft 41 deviates, especially It is to deviate relative to rotor mast 21 in the vertical.Stand 23 is fastened to the front waist section 22 ' of flat cover, and whirlpool Turbine 40 is secured to the rear section 22 of flat cover 22 ".

Therefore, engine housing 42 deviates relative to stand 23 in the vertical, and does not connects with this stand 23 Touch.

This layout makes it possible to special arrangements thermal insulation board 80 between engine housing 42 and stand 23.

Roughly, thermal insulation board can separate turbogenerator 40 and main-gear box 20, with by turbogenerator Being isolated in compartment, compartment defines a region being referred to as hot area.

Such as, thermal insulation board then has multiple panel 81,82,83, as at engine housing 42 and stand 23 Between vertical panel 81, the horizontal panel 82 between end face 24 and the turbogenerator of flat cover, The side 22 of engine housing 42 and the flat cover 22 " vertical panel 83 between '.

Additionally, this layout makes it possible to install at least one rotary decelerator level 25, it includes the band of major diameter The wheel of tooth, it is referred to alternatively as bull wheel 26.

Then the output shaft 41 of turbogenerator 40 can engage bull wheel 26 directly or indirectly.

Therefore, this power-equipment includes that the groove between output shaft 41 and main-gear box 20 connects 95.

Groove bindiny mechanism shown in figure 6 includes the groove end piece 95 being fixed to output shaft 41.This groove Stricture of vagina end piece 95 the most then becomes a part for output shaft 41.

Additionally, this groove connects can also include a flywheel 30.Flywheel 30 has drive part 32, its By the operating collaborative with secondary part 33 of roller or wheel 31.Flywheel 30 can also include being placed on drive part Bearing arrangement 34 between 32 and secondary part 33.Bearing arrangement 35 can also guide the rotation of drive division 33 Turn.

The groove end piece 95 of output shaft 41 then drive part 32 with the flywheel 30 of main-gear box engages. The secondary part of flywheel 30 then engages with toothed wheel 26.

Turbogenerator 40 can also include a dynamic seal part 85, in being used for making turbogenerator 40 Formed between medium EXT outside portion INT and turbogenerator 40 and seal.Output shaft 41 is through this power Learn sealing member 85.

With reference to Fig. 1, the secondary part of flywheel 30 can also engage with gear to rotate asessory shaft 36.Such as, This asessory shaft is for rotating rotor to control the yawing rotation of aircraft 1.

Therefore, this layout makes it possible to obtain the power-equipment with close-coupled turbogenerator, this whirlpool Turbine in height stretches out power-equipment from the flat cover of main-gear box.

Additionally, this layout is for making the impact installing heat exchanger 60 on turbogenerator minimize.Heat is handed over Parallel operation 60 stretches out from turbogenerator 40 in the vertical, lines up with turbogenerator 40 and rotor mast 21 A line.

Therefore, rotor mast 21 is in the vertical in the front of turbogenerator 40, and heat exchanger 60 is vertical Upwards at the rear of turbogenerator 40.

Therefore, the invention allows to provide a kind of close-coupled turbogenerator, it can be worked in coordination with heat exchanger Operating.

Turbogenerator 40 can include the gas generator being arranged in engine housing, in order to drive output shaft.

This gas turbine 50 includes the gas generator followed by least one turbine.Gas generator is from turbine The medium EXT of external engine sucks fresh air to produce the heat making at least one turbine 53,54 rotate Gas.Thus, gas generator comprises and has the compressor 51 of at least one compression stage and comprise combustor 52.

Turbogenerator also has the driving turbine 53 being connected to compressor and the work being connected to working shaft 55 Turbine 54.

Gas turbine in height extends.For example, combustor is positioned at more than described compressor, and work whirlpool Wheel is positioned at the top of combustor.Working shaft then through combustor and compressor, is parallel to rotor mast 21 and extends.

This working shaft 55 also can overlap with output shaft 41.

But, reducer gear 45 is placed in engine shell 42 alternatively, is positioned at working shaft 55 and output shaft Between 41.Therefore, decelerator 45 can include gear 46, for driving output shaft under the driving of working shaft 41。

Similarly, can include gear 47 at turbogenerator, it engages also with the jackshaft 55 ' of gas generator It is mechanically connected on adnexa 48.

With reference to Fig. 3 and Fig. 4, engine housing 42 be divided into around gas turbine turbine case 43 and around The speed reducer housing 44 of decelerator 45.Gear 47 may be provided on speed reducer housing.Turbine case then has Around the top casing of gas turbine, the lower case of speed reducer housing composition round decelerator 45 and around It is connected to the gear of adnexa.

With reference to Fig. 1, heat exchanger is intended to heating fresh air, and before penetrating combustor, fresh air is fired The compressor compresses of air turbine.

In this case, heat exchanger 60 includes heat exchanging region 64, and heat exchanging region 64 is by compressor 51 supply fresh air via the first inlet tube 61.Heat exchanging region 64 is then combustion via the first outlet tube 62 Burn room 52 and supply hot-air.

For heating fresh air, heat exchanging region 64 supplies from gas turbine via the second input pipe 63 Hot gas.Hot gas is discharged via the second outlet tube 65 in air in heat exchanging region 64.

About the detailed description of heat exchanger, refer to document explanation.

Additionally, the power-equipment 10 shown in Fig. 1 has the first lubricating system for lubricating main-gear box 20 110.This first lubricating system 110 is such as used for injecting mineral oil to flat cover 22, to lubricate speed reduction The gear of level 25.

Similarly, this power-equipment has the second lubricating system 120 for lubricating turbine engine 40.Should Second lubricating system 120 is such as used for injecting artificial oil in engine housing.

Additionally, this power-equipment can be fastened to the platform 6 of aircraft by suspension arrangement 30.For example, Suspension arrangement 130 includes hanger bar 131, and hanger bar 131 tilts to extend to support platform 6 from stand 23. Suspension arrangement can include shockproof component.

Additionally, suspension arrangement 140 can be selectively placed between flat cover 22 and support platform 6, such as, Bottom surface 24 " and between supporting platform 6.

Although power-equipment is hung, but, it keeps static relative to support platform, in this sense, Power-equipment does not have the component of any shake, such as, moves to provide from the position providing lift by rotor The position of pull strength.

Therefore, stand and turbogenerator are static relative to flat cover, and they do not tilt.

Certainly, the present invention can carry out multiple change and implements.Although several embodiments being described, It should be readily understood, however, that, exhaustive all possible embodiment is unthinkable.Certainly, Ren Heneng The equality unit of the device described by replacement is all without departing from the scope of the invention.

Claims (17)

1. a power-equipment (10), has a main-gear box (20) and turbogenerator (40), Described main-gear box (20) has substantially vertical rotor mast (21) for the oar rotating rotor (2) Hub (3), described turbogenerator (40) has output shaft (41) for driving described main-gear box (20), Described power-equipment (10) has heat exchanger (60), and described heat exchanger is fixed on described propeller for turboprop On machine (40), wherein:

Described main-gear box (20) has at least one rotational delay level (25) being arranged in flat cover (22) With the stand (23) on the end face (24 ') standing upright on described flat cover (22), described rotor mast (21) Through described stand (23)；

Described turbogenerator (40) includes that engine housing (42), described output shaft (41) stretch out institute State engine housing (42), when described engine housing (42) is arranged on described end face (24 '), Described output shaft (41) inserts in described flat cover (22), and described output shaft (41) is basically parallel to institute Stating rotor mast (21), described engine housing (42) deviates described stand (23) and not in the vertical Contact with described stand (23)；And

Described heat exchanger (60) is at the rear longitudinal extension of described turbogenerator (40), described rotor Mast (21) is placed longitudinally is positioned at the front of described turbogenerator (40) in the opposite direction.

Power-equipment the most according to claim 1, wherein, described power-equipment (10) includes heat insulation Plate (80), described thermal insulation board is arranged between described engine housing (42) and described stand (23).

Power-equipment the most according to claim 1, wherein, described flat cover (22) is described by carrying The front waist section (22 ') of stand (23) to the back segment portion carrying described turbogenerator (40), (indulge by 22 ") To extension.

Power-equipment the most according to claim 1, wherein, described turbogenerator (40) includes tool There is the gas turbine (50) of gas generator (51,52) and be fixed to the work turbine of working shaft (55) (54), described working shaft (55) is basically parallel to described rotor mast (21).

Power-equipment the most according to claim 1, wherein, described turbogenerator (40) includes one Individual reducer gear (45), described reducer gear (45) be placed in described engine housing (42) and It is positioned between described working shaft (55) and described output shaft (41).

Power-equipment the most according to claim 1, wherein, described turbogenerator (40) includes moving Mechanics sealing member (85) is with by internal for described turbogenerator (40) the medium isolation outside with it, described Output shaft (41) passes described dynamic seal part (85).

Power-equipment the most according to claim 1, wherein, described power-equipment (10) includes connecting Device, for described engine housing (42) is fastened to described flat cover (22), described connection fills Put and include bolt ring (90) and multiple centring pin (91).

Power-equipment the most according to claim 1, wherein, described power-equipment (10) includes described Groove bindiny mechanism (95) between output shaft (41) and described main-gear box (20).

Power-equipment the most according to claim 8, wherein, described groove bindiny mechanism (95) has Being fixed to the groove end piece (95) of described output shaft (41), described groove end piece (41 ') is with described Flywheel (30) engagement of main-gear box (20), described flywheel (30) engages with rotational delay level (25).

Power-equipment the most according to claim 9, wherein, described flywheel (30) engagement bull wheel (26).

11. power-equipments according to claim 1, wherein, described output shaft (41) stretches out described Engine housing (42), it stretches out height (H) more than 10 centimetres.

12. power-equipments according to claim 1, wherein, described power-equipment (10) has use In lubricating first lubricating system (110) of described main-gear box (20) and being used for lubricating described turbogenerator (40) the second lubricating system (120).

13. power-equipments according to claim 12, wherein, described first lubricating system (110) Including mineral oil, described second lubricating system (120) for lubricating turbine engine includes artificial oil.

14. power-equipments according to claim 1, wherein, described stand (23) includes hanging dress Put (130), for described main-gear box (20) is suspended on support platform (6).

15. power-equipments according to claim 1, wherein, described stand and described turbogenerator It is fixing relative to described flat cover.

16. 1 kinds of aircraft (1), have lifting rotor (2), and described lifting rotor (2) includes propeller hub (2) and multiple blade (4), wherein, described aircraft (1) includes according to claim 1 dynamic Power equipment (10).

17. aircraft according to claim 16, wherein, described aircraft includes carrying described power The support platform of equipment (10), described power-equipment is static relative to described support platform.