DE1481654A1 - Drive unit, especially for combination flight screwdrivers - Google Patents

Description

H8165A

Dr .-! N'j- H Ι ^χ> ''". ₄ «.

jws'- ' ^{m {} " ^r , ₃ May 13, 1968

iAt

Specimen copy]

May not be changed!

Boolete Charles HARCHBTTI Drive unit. in particular

The fire tuvr is based on a drive unit, • In the engine for the propulsion of an aircraft ”or fsheugs voist, because it drives a compressor that rarely supplies compressed air, possibly in variable amount and speed and old variable pressure,” drives a RH freeze serves. In particular, but not out of the ordinary, the fiery tune looks at a drive unit for the gate drive and the rotor drive of a Reectione-KoBblnatIotas flight.

Ss let known »d« J3 ο in Hubschrnuber a gevieee upper Orense has a high degree of efficiency, about the same as aerodynamic efficiency decreases very quickly. Above this oronee is the tear-off the training results in stronger vibrations, the Luftfaha »» Seug nloht more geet «can be and bie

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BAD ORIGINAL New documents to. ■ i..u ...: ■ -ir ι «,,: /». ·. λ · ..., ■ _; -.g - *. ν

U81654

Koepr »salichkeitephünom« ne occur ·

A solution that has been taken into consideration by moving this (Jrenae) consists in relieving the rotor both το «lift al *" ach to * gate drive tu, "blaze bmui sB" a wing and an auxiliary cable drive, such as ζ Yes. provides for a propeller or a two-rotor engine, etc. »

In the case of a Reactiona helicopter, i.e. a helicopter, whose rotor is driven by thrust nozzles on the rotor blades or aa corresponding nozzle arms, is the embodiment su a combination a-flight screwdriver easy. Bs 1st namely known that a Tenrendetee for the propulsion or Zveistromtriebverk also as Brcvuger dea pressure medium for the Drive dea rotor «can be used.

With a RealctloxisrKorabinationa-Flugeohrauber with a through a "cold" flow medium driven reaction rotor is the Sefcundlretröaunf for the "Rubaohrsiuber" flight «guided» to the rotor xduring the tranelation flight dl · BekundUretrQnune since * u is used, a sueätsllotaen propulsion thrust look out »that comes down to the de3 Primftratromes.

Although this lorning has the advantage of simplicity »let the efficiency of lower oils with a combination -? lu £ »a about with meohaniechem drive. Which for a rotary wing aircraft should - Algae 'horizontal speed determines a relative speed low flow rate, and tiomit a low

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BATH ORIGINAL

Pressure of the OekuodärotrÖsiune, which, however, don’t buy air for the DrehfItigal liofert · In 6ep, ensatr. this is what the drive needs de «Rotors a higher pressure of the flow so that the butter or Arne dos Rotor «remain in acceptable proportions.

Another solution is to have a friobverk with a « Provide a compressor and a propeller that can be connected to the engine directly or via a gearbox. In order to do so su relieve and Uta the Vlrkungarad «u erhShsn, aiad im generally also provided clutches. Without such a coupling, the propeller would turn with the Sonkrochtflug and - Consume energy. During the Branelatlona flight, that would be the same in this area of the air supply they are closed off Compressors run along and damage energyThis solution is sure to bring good efficiency even at low speeds, but has the disadvantage of complication.

The purpose of the present invention is, in particular, to unite good efficiency with a fine, simple solution.

In this case, according to the invention, ease is forgotten that at the inlet of the drive unit, the compressor - a fan forming blades - are arranged on at least one part of the first stage and on the other part - a double system of adjustable Ijslteo blades to control the total output

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Luftstromeo zurKGu £ ung ainee slipcase as well as sa * control of at least a part of the «red stage of the compressor is provided for the drive of the auxiliary device, so that a twofold adaptation to the desired movement or flight suatarjd by Beaufohlagungsetsteuerung the OeblUaeo and / or the compressor is more accomplished, ie depending on whether the engine is used for locomotion or for driving the auxiliary device.

When used in a Reaction Koinbinatlonß flight wrench That the drive unit is constructed according to the invention, that the auxiliary device is the reaction engine. The air supply control of the fan and / or the compressor is carried out depending on the state of Khiga.

So while with the known solutions either the engine was built for the Tranelatlon flight, «it was a bad one Vi degree of deviation for vertical flight, or for vertical flight with a poor degree of efficiency for the separation flight or but for a mediocre efficiency for both Flugeuettode, let · ■ gemftfl The door lying location is possible, an adaptation de «Drive units on both Tlugzuetlnd · old one Efficiency suitable for both flight conditions «durohsufUhr ^ n ·

OeoHB a Aueftihrungeforai let the invention that medium 8 of the Le it shoveling in vertical flight, the air supply fan eum abgappcrrt 1st wälurend Bruckluftetroa of the compressor is driving the sun Rotorn, and when separation

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U81654 - 5 -

latloneflug the air supply to the compressor at least · part «·! ·· gsdxo is old, while the fan generates «air flow sur Generation of an additional T'MftlllT ^ t

Advantageously, the drive unit according to the fourth invention is like this trained that means are vorgeaehon that also in translation flight the pressurized air flow generated by the compressor to generate one too accurate thrusts, preferably after partially empty Throttling of the air supply to the compressor by means of the Ielteohttttfein, make useful.

An advantageous design of the drive units according to the invention is also given by the fact that at least the first stage of the compressor comprises three concentric shovel cranes, of which the Ana forms fans and blocks the air supply by means of a first guide vane iet _f of which the second forms a compressor "the central duct" Htranz "e is also shut off from the air supply and supplies the air flow for the drive of the auxiliary device, and the third supplies compressed air for the turbine of the engines.

the invention can also be provided that the engine has a free-wheeling turbine, and that the part of the Compressor with the compressor stage or stages, which the Oebläaeechnufeln wear, from the utility runner of the? reilaufturMiko driven in let, wührond the other part of the compressor with the blades to generate the compressed air stream for the

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Auxiliary device driven by the compressor's engine is.

A favorable design of the drive unit has been achieved the invention is also given that the compressor ■ it one, and the same shop oln without subdivision of the aohaufeln both the compressed air for the auxiliary device as also generated for daa engine, with the compressed air fttr the auxiliary device behind the corresponding pre-sealing stage entnoanen and for the tranlation flight at a lower one Remove the stage and add the air generated by the blower et ro « is suggested.

Further herbalities and advantages of the Ii rf indune arise See the following description of several implementation examples of the invention in connection with the drawing “Be”

? i #> 1 a Sohnittaneioht a erfindungsgenttfien drives aggregates genrflß a first AusfUhrungsbeieplel seen from the side la Ba! b "ahrm £ b9rwiamtmAt

Yig · 2 is a flat sectional view of the same exemplary embodiment from above in the advance mode

3 shows a sectional view of a further exemplary embodiment of the invention from the side;

4 shows a 3-section view of the drive according to the invention. agffregnte nnch? ig 3 from above;

Pig. 5 an echematic representation of an inventive

ORIGINAL

H81654

a third quote;

. 6 is a sectional side view of one According to the invention, drive units old one open-air turbine, gealfi an ized embodiment and

fig «? "Ine Boteltten" not the introduction of Fig. 6 τοπ above.

In Fig. 1 and 2 shown erfindungegeeäS * Astriebe * aggregat veiet «In Turblnentxlebverk 1 euf, da * a Terdirhter drives »B Svieonen de« Terdicbter and the Turblnentriebwark A cap can be switched on, especially if it is calibrated It oscillates over a Unvelle turbine. Venn However, the drive alttele a · lurbiaantrlebwerka ait free running Turbinealittfar If such an application occurs, it is generally unnecessary.

The compressor has at least two stages. Of simplicity half of the harvest stage rewarded with *, passing the wide state is rewarded with 5 1st. With thieves with The larger number of stages indicates 4 Always the first stages and 5 all other levels.

As a result of the invention, the crane »of the first * 9tmfa (61er the forces of the stages reap) of the compressor «anaselnem extent Sobjnafeln 6 of a fan. Aa inlet dea drive units

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BATH ORIGINAL

H81654

is also a double ring of adjustable blades arranged, which form the guide vanes for the compressor} The UuQere Kranr 7 is used to control the air supply for the fan 6, the inner crane 8 guiding the air supply controls for the compressor. The blades of the wreaths 7 and 8 Bind will smell a "fully open" position in which the ele allow a maximum amount of air to flow in, and a closed position, in which they prevent air from entering naxinally, can be locked.

The energy of a turbine engine 1 can flow onto this y / eioe via various controllable air flows. The air flow f1 is supplied by the blower 6, while the flow tZ is supplied by the two stages 4, 5 of the compressor.

When it comes to equipping a coalition robber old of a great invention, the 8troa \ Earth through one or more thrust nozzles 10. D ·.-Through creates a susUtalicher thrust gu da * thrust, the duroh the relaxation of the oasis leaving the turbine is flooded The current f2 can be derived Ubor a line 11 and To drive the Rotora 12, recoil can be used.

The Stron f2 is operated in a "helicopter" mode from benefit st. The shovels of the outer garbage 7 are opened up, while the shovels of the inner neck 8 open.

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H81654

Bet tind. The compressor 3 works at this level with all stages and supplies a current Ϊ2 to the Botor 12. (Ig »Ό

In the case of »translational flight, on the other hand, the blades are de · / inside Xransee β closed while the fkthaufflA.de · iuBeren Irans 7 open elndr The compressor is idling, and the fan 6 generates an additional 3 stroke. blaze the Current fi through dl · aehabdüee 10 aueetöBt. (fig. 2)

Wthrand de · Anlaeeene de · Drive units and the show » fine both erase chambers 7 and 8 closed. Xp let but SBgXIaIi, dal The Botvendlg »loergie nirhtedeetoireniger eehr there is great, especially vean ·· eich u »ein. »Iawellenturtin ·» - trlebw «rk acts. In this case let compressor J wipe and the turbine ventilator 1 switched on clutch 2

Self-reliance on the area around the area of the Torbia Ausstesndan gases through suitable WsJnilwwi achfltMa, «1 · ··! · duroh AbcasstrahlftShruns; by means of the e fi, dttrob «achrertnung or simply by mrnAnmff of printing on the emmfam duroh a corresponding choice of the mehmb

THe "rfindung ·· permitted thanks to the Ünlauf de · Amtrl ^ b · - agspregats arranged forriohtung, dl · beidau etrte · fi""A Vt oneness su control and insbeeondere regain its pressure below, represents the Procyon or la dam Qeblese effective will. From # r llehe * ObarragungBgetrlebe or any other Obermeti

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organ avoided ♦ The form of operation described above remains but a loss of thrust in translation flight due to the extensive £ p9Otribiig of the compressor 3. One can indeed use the remaining current f2, (which then has a low pressure), direct into the hotor, around a 71tt0fo & 9 «uf« rM0taai nex *> «l« aifl * il «u but the efficiency of a single solution would be low.

At the in? I £. 3 and 4 is again the double adaptation to the plug-in configuration by the control density of the two streams f1 and f2, as shown in FIGS. 1 and 2, but an improvement is provided for the translation flight, both of them Stope f 1 and f2 sur ürseuguag a «slide can be used. For this purpose, in addition to the components described in danionon, which bits are denoted by the same reference as in the Pig. 1 and 2, susätslioh on the one hand a different thrust nozzle 13 lying parallel to the thrust nozzle 10 for the Auasto deo stream f 2 and on the other hand a system of flaps 14 »sliders or the like tZ is steerable either through the line 11 into the rotor or into the thrust nozzle 13.

With open blades of the inner crane β 8 and closed by the nozzle 13 of the KLappenayaten 14 "through the stages 4, 5 de Verdiohtero highly compressed stream ti and most favorably ig sug the rotor for the drive via the line 11 'is ~ leads. The 3cnnufeln of the outer ring 7, as shown ohematically on the left τοη? Ig _n 3, are closed and

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d * r loablnatlone-Flueeohrauber works la "helicopter * ··
! • trleb.

On the other hand, up to frtnalatlenflug the blades of the foot are open. The current sucked in by the sound of the sound fi Will aleo flow through the SetxuMüi? 10 soft tone. Bel tellweiee geachloeeenen shovels de «inner« »cranes * α θ and at d * r Offauzkg * at« lluag de · Happeneyete »· ft the inlet sur DÜae 13 ^ ff "sl" t, the terdichter 3 will not "roll" if Loft beaufectilaft "8 · 1η pressure can thereby eof the pressure de" through da * Oebläee 6 • e "" ten etvotje " be changed »and the Strne tZ
through dl · ephubdü ·· 13 auegeeoboben and forms a su «ltill * | #h «n thrust BU de« thrust generated by the fan β.

On dl · «· Velee let dl · aazlmal necessary performance for
da · ftebll · · and the Ter Dichter geoeineaae Leletung in all
Flugvuetinden he · resembles, uztd dl · mating the ihurbln · can easily be accomplished. VI · Is the previous case can door you lupplung tempering "In · 2 eeln necessary w" if. «La Hnwelleavfurblaeatrl« bv «rfc Torgee« hen lat, e «lb» t «tan dl ·
d «r KrinjM 7 and β rBllig fex & lo ···» become.

At elnea fr «ll« ufturblnentrl «bw« rk you can do the matching
by · 1 &# Oeachwladigkelteanderune d ·· Huteleletunfello
the turbine and the wind turbine powered by the dleaea

BATH
£ 109 812/0300

Compressor 4 - Ck «blane 6 are fully strengthened - With eechloesenen Echnufeln dos outer rims 7 the power absorbed by the blades of the fan 6 is lower; the speed dee blower is therefore high etf * nao as the dee from stage 4 Vordichtere delivered pressure This rfirkun # adds to the der'Öffnung of the blades 8 and results in a higher pressure in the compressor _v In TraneTationsflug but oind the blades outer deo Krar. It is therefore possible to use a lower speed at which the pressure of the fan 6 becomes lower. The air supply through the ring 3 can therefore be weaker than at a constant speed, and the degree of effectiveness of the

• Be rushed.

In Fig. 5, an embodiment is shown in which no Clutch is necessary. The turbine engine is also simplified, and the compressor is used for a first compression of the air for the turbine.

In this embodiment, the compressor has 5 alternate stages 4, 5 on. There are also two withdrawals at 14% 14 " Compressor provided. Takes place during the "helicopter" flight the air extraction through the extraction at part 14 '. There is ice Part of the air is fed to the rotor, while the other part of the air is fed to another non-visible compressor of the turbine engine is fed in * This second compressor could

be a fiftdial compressor
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BAD ORiQiNAL

When Tran3lationsflu £ i.st unlike de au removal site \ ^i% geschlooflen while the Bntnnhranatelle 14 ", the odor after the first stage dee the harvesting stages Verdichtere let disposed is opened and discharges air into the exhaust nozzle IO, as well as the OebJäge 6 Θ3 does In this case, the blades of the ring 7 of the stator are open, while they are closed during vertical flight.

In the embodiment shown in FIGS. 6 and 7 the general training according to Figo 1 and 2 -taken and adapted to an engine with a free-wheel turbine, the additional " offers lent possibilities.

The free-wheel turbine, generally designated 30 int, veiet a hat power runner 31, which via a shaft 32 the first stage 4 or the first 8 stages 4 of the compressor 3 drives o This stage is formed from three Sohaufel wreaths » namely from an inner crane 4, an intermediate crane 4 '' der

τοπ dom is first separated by a ring 33, and «ine« let Crane * 6 separated from the previous one by a ring 34 and the fan forms.

The compressor rotor 35 of the engine carries on the one hand a high pressure compressor 36, such as a HAdial compressor, and on the other hand drives the second stage 5 of the compressor «3 (or the stages following the first stages). This second Step is formed from two blade rings, namely from an inner wreath 5 and an outer wreath 5 ', which is

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: ',. BAD ORlGlNAU

first separated by a hanging 37 "

A tube 38 extending the ring 34, in which the "wide 3 stage 5 of the compressor 3 rotates, stands with the to the rotor 12 leading line 11 in connection and has at its rear End of a system of flaps 14, slides or the like. on"

A flow channel closes at the Rinc 37 of the second stage 5 39, which pre-compressed the from the inner rim 5 Directs air into the high pressure compressor 36.

Finally, there is a flap 40 for closing the line 11 provided.

At the inlet of the drive units, two blade rings 7 and 8 are again arranged in such a way that the outer ring 7 controls the blower 6, while the ring Θ ^{controls the air supply for the rings 4 * and 5 1 of} the compressor 3. In this way, the two flows f1 and f2 can be controlled »while a third 3troo f3 is pre-processed by the rings 4, 5 of the compressor 3 into the high pressure compressor 36 and is used to drive the turbine»

^N leg Hubechrauber "flight, the blades of the collar 8 are opened while the blades dee rim 7 are closed" as shown sohematisch in Fig. 6 * The air is in the rims 4 '# 5 * of the compressor vordichtet <> where the aind Flaps 14 closed (Figo 6), while the flap 40 is open

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net ltt, so that the current f2 via the line 11 den saga is led. The frills 4, 5 conduct the current f3 undisturbed the turbine «u-

Beta starting the turbine will also be the blades de * Kraasee 8 closed, so that the compressor rotor 35 only is loaded by the blades 5, which are also not acted upon “This means that there is no problem when starting.

In the case of vertical flight, unloaded airflow behind the crane * 7 means a loss. However, if the duration of this flight pleasure is relatively short, this has no noticeable consequences for fuel consumption. Its influence on the propulsion power is also small if the engine is designed for high flight speeds.

During a translation flight, the portion 40 is the whole or most of it closed so that the rotor does not get any air » Furthermore, the blades of the crane 7 are fully open while the shovels de «franse * θ are partially closed. (Fig 7)

The öebllee 6 then creates a stroke with a large flow rate but low pressure. Through the Irans * 4 ' ₍ 5 * a current tZ is generated which has a low flow rate and a low pressure.

The current f2 can be mixed with the current f1 from the fan.

BAD ORtOINAL $ 09812/0300

some and form a thrust at the nozzle 10. Possibly you can also separate these two currents f1 and f2 Let the thrusters come out.

In the training described, there is the essential inventive modification of a conventional twin-shaft drive that is, the fact that the groove power rotor 31 is part of the compressor the turbine drives and that the compressor rotor of the turbine sum a part of the compressor for the compressed air supply Rotor drives.

If one or more axial compressor stages are arranged on the compressor rotor, one has the possibility of starting supersonic speeds to achieve what would be impossible, when this compressor stage on the outer circumference still the blades for the fan 6 had to carry. The power required for the width stage 5 ′ of the compressor 3 is of the same order of magnitude like that of the first stage 4 for the air supply of the turbine, so that a power balance can be easily maintained can ο

The last-described training of the invention The drive unit allows installation in already existing twin-shaft turbine engines and therefore facilitates production.

The hangers 33 and 37 and the tube 38 prevent mixing of the current f2 or the currents f 1 and f2 with the current

909812/0300 BADORLGiNAL

f3 for the air supply to the turbine. The one for the compressor runner 35 required power is greater in vertical flight all during translational flight, since in the latter case the outer one Wreath 5 'of the second stage is only partially loaded »other side lot the load on the power rotor 31 at Translational flight greater, because this then simultaneously the fan 6 and the partially loaded middle ring 4 * the firstΛ stage must drive. The total power of the engine can be the same in both flight states.

All from the description and the drawing, including the structural details, emerging features can also be essential to the invention in any combination be.

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Claims (1)

Specimen copy Darts cannot be changed P 1184-23 / fc Societe Charles
MARCHETTI Claims (1 ^ drive unit, which uses a drive unit to propel a » Vy ^ euge an aviation vehicle or vehicle that also has one Drives compressor, which is used to supply compressed air to drive an auxiliary device, characterized »That at the inlet of the drive unit on the one hand at least at the first stage of the compressor A fan forming blades are arranged and on the other part a double system of adjustable guide blades to control the air flow directed towards the fan for generating a thrust and for controlling the at least part of the first stage of the compressor Air flow provided for driving the auxiliary device is, so that a twofold adaptation to the desired movement or plug state by load control the fan and / or the compressor »manageable depending on whether the engine is used for locomotion or to drive the auxiliary device ο 909812/0300
New documents (αλ. 7 1 1 au ·. 2 ν.-, ι s · «3 jm ämv Un ₀ ^ *.«. 4. & im7) H81654 2 «drive unit according to claim 1, for a reaction Koabinatlone flight wrench, characterized in that the auxiliary device is ale reaction heater of the helicopter is trained. 3 · Drive unit according to claim 1 or 2, characterized in that by means of the guide vane ^ during vertical flight the TAift feed is shut off at QeblS.ee while the compressed air flow of the compressor is used to drive the rotor, and during trans1ation flight the air supply to the compressor is at least partially shut off, while the air flow generated by the fan to generate an additional Thrust serves 4. Drive unit according to at least one of claims 1 to 3, characterized in that means are provided which are also used by the compressor in translational flight generated pressure air flow to generate an additional Thrusts, preferably after the partial throttling Pile air supply to the compressor by means of the Lei tea, usable do. 5. Drive unit according to at least one of claims 1 to 4, characterized in that at least the first stage of the compressor comprises three concentric blade rings, one of which forms the fan and the air supply by means of a first fan blade ring 9098 12/0300 _{ΛηιΛ1ΜΜ} BATH ORIGINAL U81654 "20th is lockable, of which the second one. Compressor forms, by means of a second guide vane ring «.«; can also be shut off from the air supply and the air flow to the ' drive of the auxiliary device supplies, and of which the third supplies compressed air for the Turtine do.s engine 6, drive unit according to less, ena one of claims 1 to 5 _t, characterized in that the engine has a free-wheeling turbine, and that the part of the compressor with the compressor stage or stages which the carries bsvr. Fan blades / wear, from the useful power of the Free wheel turbine is driven while the other part of the compressor with the blades for generating; un £: the pressure i Turbines— "" air flow for the auxiliary device from the compressor * rotor of the engine is driven, Ir drive unit according to at least one of claims 1 to 6, characterized in that the earnings, ter with one and the same blades without subdivision The blades generate the return air for the HOfs-vomchtung as well as for the engine, whereby the compressed air for the auxiliary device is taken from the corresponding compressor stage and for the translation flight at a lower stage entachakflr and the air flow generated by the Gobiäse can be touched . 9 0 9812/0300