DE1401273C - Gas turbine or other internal combustion engine power plant for aircraft - Google Patents

Description

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The invention relates to a gas turbine or laßmotor energized to pump the fuel other internal combustion engine power plant and the compressor via the gear plane with at least one auxiliary device that drives directly and via the compressor shaft and the a differential gear is driven, via the differential gear drives the gas turbine. As soon as also the cranking motor of the engine to effect 5 the gas turbine is running, the brake is released and the comes. Starter motor de-energized.

As is known, the engine speed changes at The invention now relates to a development of the

an aircraft, depending on whether the aircraft is the last-described engine system with the one

is on the cruise, starts, climbs or is connected to the auxiliary device via a differential epicyclic gear.

Landing is approaching, within wide limits. Correspondingly, via which the cranking motor of the

The drive speed of an engine also changes accordingly. The invention lies

connected auxiliary device. In the case of one of these, this is based on the task of making the arrangement in such a way that

Power generator as an auxiliary device is particularly uncomfortable that the cranking motor is in operation of the engine

because it is precisely the highest electrical power that can be used to drive a

Operation of the most varied of power-operated on-board 15 auxiliary devices, for example to support the

facilities when hovering for landing, i.e. drive connection between the engine and the

a low engine speed is required. To relieve the auxiliary device or the auxiliary device when changing

About the difference between the engine speed changing engine speed with constant speed

number and to operate an auxiliary device.

To compensate for the required speed, one has at 20 this problem is solved by the a known internal combustion engine three outwardly leading members of the differential (USA.-Patent 2 485 126) on the shaft of the epicyclic gearbox, the first with the engine auxiliary device a speed sensor connected, the motor, the second with the cranking motor and the a hydraulic pump controls, which in turn unite via a third party with the auxiliary device in constant drive hydraulic motor to the differential gear 35 is binding and that the rotatability of a Geeine Additional movement granted to the speed of the drive member between the first and the second Auxiliary device to keep constant. This hydraulic outwardly leading link on its own axis Control device takes up a lot of space and can be locked by means of a retaining device, wherein is relatively complicated and, accordingly, the retaining device is susceptible to failure from one to the speed of rotation. 30 speaking device in locked position for so long

In the case of a gas turbine system for driving a one is kept, as the engine speed under power generator, it is already known to upright a predetermined value,
Maintaining a constant speed of the Stromer- With this arrangement, it is possible to switch the rotary generator with changing loads (German patent number of the auxiliary device, e.g. a power generator, writing 922 870) between the gas turbine, which is set at 35 by changing the speed of the The starting motor and the compressor of the system is directly coupled, and depending on the speed of the engine to the power generator, a continuously controllable transmission flows, for example, to provide the speed of the power, the generator is connected to the

A propeller turbine engine must also be kept constant.

with two independent turbine rotors 4 ° The device according to the invention has, however has been proposed, in which an oil pump not only has advantages in a power generator as an auxiliary Lubricate the bearings from one device to the outside, but also, for example, from a hydraulic feeder Link of an epicyclic gear driven like pump as an auxiliary device. Namely falls with one of the is, the two other outward leading Glie aircraft engines from a hydraulic pump, so the door that drives the propeller shaft can be used with another engine without a connecting rotor or the two independent changes in the engine speed via its antenna Turbine rotors are driven (German rotary motor, the hydraulic patent driven by this 1 031 058). The purpose of this arrangement is to allow the pump to operate at double speed so that this can occur that the oil pump in normal operation with a pump that of the pump of the failed driving force half of the total of the turbine rotors corresponds to 50 factory additional delivery rate. Depending on the speed and the failure of the turbines Hch, the situation is when the drive and propellers, which continue to run due to the airflow, work instead of hydraulic pumps with direct current generators The oil pump can still be driven at half the speed of the gate, which is also used at Propeller corresponding speed is driven failure of a generator the other with higher and ensures the lubrication of the bearings. 55 speed must be operated to match the voltage

Furthermore, a gas turbine engine has to be kept constant.

system for aircraft known (USA patent specification Although a cranking

2 693 080), in which the Ciasturbine one after the motor is desired, the speed of which is continuous

outside leading link of a differential gear is changeable, the new device can also

(rubs and the other two outwardly leading 60 advantage in cranking motors with constant speed

Cilicder of the differential gear are used for the compressor, the torque of which is at constant

Drive the system or the power consumer. ter speed is changeable to z. B. Fluctuation

There the fuel pump is driven by the shaft of the gene in the power demand on the

Compressor driven by a gear train to largely compensate for auxiliary equipment,

whose Zwisthenwelle is with the wave of an electric 65 By the measures according to the invention

see starter is coupled. For starting the one simple and versatile in usability

The installation is the creation of the groove / performance facility with which the performance of a

of the differential gear te, (held and the auxiliary device completely independent of the rotary

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number of the engine produces the respective requirements. The front end of the shaft 15 is over

can be customized. a wedge, not shown for the sake of simplicity

The arrangement according to the invention can be toothed with the arm star or planetary gear

be affected that it is connected to the auxiliary device in drive carrier 21 of epicyclic gear 14. This

The link connected to the input link 5 epicyclic gear is constructed as follows:

a second epicyclic gear is firmly connected, one connected by the impeller 36 of the turbine 13

whose second outwardly leading member also driven shaft 33 carries a sun gear 32, which with

with the engine and its third after three planetary gears mounted in the arm star 21

outside leading link with the auxiliary device in 28 combs. Each of these planetary gears 28 is with

drive connection is, with the speed an- io a smaller planetary gear 27 firmly connected,

speaking device of the third member of the or it consists of one piece with the latter; the

second epicyclic gear is driven. Planetary gears 27 mesh with an internal tooth

The starter of an engine via a two-stage ring 23, which is connected to a second internal ring gear 24

figes epicyclic gear to be effective, with a larger pitch circle diameter from one

which is also connected to an auxiliary device, there is 15 pieces and together with the latter one

an engine with a propeller known (German ring gear ring 22 forms the ring gear 24 stands with

Patent 738 877). In fact, there is one at three planetary gears 26 in mesh, which also

Lasser used, which decouples automatically as soon as 21 are stored in the arm star. Each of these planetary

the shaft driven by it has a higher rotating gear wheels 26 with another planetary tooth

number takes as its own. In this known ao wheel 38 is connected or consists of the latter

The engine is a pure occasion in one piece. These planet gears 38 drive a sun

direction. Namely, between the engine motor nenrad40, which is loaded at the end of a hollow shaft 42

and propeller is a common propeller undersized, which has the runner at its other end

Setting gear in the form of a two-stage circulating power generator 12 carries.

gearbox, to which the starter motor with 35 the sun gear 32, the internal ring gear 23 and an overrunning clutch is coupled and that with the arm star 21 thus form the three through which an auxiliary device, here a pump, is constantly connected to planet gears 28 and 27, there is a drive connection to the outside. This pump actuates a leading member of a first epicyclic gear 14 A braking device, which brakes a member of the epicyclic gear and the internal gear rim with the internal gear rim 23 and thus a frictional connection 30 ring 22 forming the internal gear rim 24, the arm star between the epicyclic gear and the drive mechanism 21 and the sun gear 40 leads the three outwards. The starter initially drives the propeller via the revolving link of a second epicyclic gear 14 B. running gear, whose inertia The revolving torque shown in the exemplary embodiment is then a double epicyclic gear when reaching a certain rotary gear 14, in which number via an overrunning clutch to spin 35 chem, the two annsterne and the two of the engine are also used. So- internal gear rims form a unit,
soon the starter motor with the screw has reached a certain The housing 48 of the turbine 13 has a rich speed, the pump output is sufficient, Hch sized annular inlet channel 50, in which the braking device gradually opens into a supply channel 49, as well as an axial one bring the positive connection 40 to the outlet pipe 51. Between the inlet duct 50 and between the propeller and motor, the turbines flowing through from the outside to the inside at the effect of the starter motor from the inertial rotor 36, i.e. a rotor of the centripetal type, torque of the propeller is supported. As soon as an adjustable guide vane ring 57 is arranged, the engine is started, the starter clutch jumps back, with which the volume and the flow direction are returned. 45 direction of the inlet channel 50 via the guide

The invention is described below with reference to the blade ring 57 for the blades 58 of the turbine

matic drawings on two exemplary embodiments 36 can change flowing air,

len explained in more detail. The supply channel 49 is fed with air,

1 is a schematic representation of the last or a high pressure stage of the dimension of the invention designed part of a gas door 50 denser of the main engine of the aircraft de-combinatorial engine for planes, and men will. To drive the turbine 13 you can

F i g. 2 shows a schematic representation of a, however, also another pressurized flow

Use a modification of the control device of the inventive means, e.g. B. another from

according to part of a gas turbine engine, engine driven compressor removed

In Fig. 1, within one with dash-dotted air, there is a flow center held ready in bottles Lines indicated housing 11 a total of tel, gas supplied by combustion chambers or Gegemit The circulating air denoted by the reference number 14, if necessary, even air compressed by the damming effect, drive housed, the at the front part of the generator 12 is so with the help of the main engine of an aircraft, in the present running gear 14 partly from the main engine Case of a gas turbine jet engine attached. 60 of the aircraft from over the shaft 15 and to the an-Das Epicyclic gear 14 is driven in part by the turbine 13 by means of one of its parts. In order to Shaft 15 from the aircraft engine and to achieve that the armature of the power generator 12 at the part of which is driven by the turbine 13. changing speed of the aircraft main engine

The rear end of the shaft 15 is at 16 with and thus also the shaft 15 with a constant

provided with a spline that rotates a connection 65 speed, and that therefore the output

with the aircraft engine, namely either the input frequency is constant, the speed of rotation is the

controlled indirectly with the main shaft of the engine or Tm bine 13 so that this speed controller

with a gear driven by this shaft of the H; iiipttrieb \ Verk> be balanced. the

The speed of the turbine 13 is determined by changing the ninstellwinkcls and the flow cross-section Changed guide vanes 57 of the turbine. The angular position of the guide vanes is set by means of a lever 61 to adjust.

The adjustment of the lever 61 is carried out by a control device denoted overall by 63, which works partly with hydraulic and partly with pneumatic power.

The hydraulic part of the control device 63 comprises a gear pump 64 which is a drive gear

66 which meshes with a gear 65 seated on the hollow shaft 42. The pump 64 sucks liquid from a container formed in the housing 11

67 and feeds them under pressure to a line 68 leading to a hydraulic actuator 70 leads, with which the Leitschaufcln via the lever 61 57 can be adjusted. This actuator 70 is pneumatically operated by a speed change responsive controller 71 controlled, the drive gear 72 of which on the power generator or hollow shaft 42 seated gear 65 is driven, so the changes in speed who feels wave 42. This controller 71 is a known controller, e.g. B. a regulator of the type shown in British Patent 760,656.

The turbine 13 serves not only to contribute to the drive of the power generator 12, but also to to start the main engine of the aircraft as Andrelimotor, and is dimensioned accordingly large. A braking device 73 for the ring gear 22 is provided for the starting process. For this purpose, the latter has a radially projecting flange 77, which acts as a brake disc serves. On both sides of this brake disc are brake pads and normally provided by springs pressed away from the brake disc ring plates 74 opposite the housing 11 are secured against rotation, but can perform an axial movement. on the one Side of the brake disks 74, 77 is in the housing 11 an annular piston chamber 79 for an annular Piston 80 is formed and on the other side a support flange 81 is formed on the housing 11.

When a pressure medium is supplied to the piston chamber 79, the piston presses the first ring plate 74 in the direction of the brake disks 77. Since this extends over the second ring plate 74 on the support flange 81 is supported, it is held between the brake linings of the ring plates 74. Since the as Brake disk serving flange 77 forms part of the ring gear ring 22, thus the inner tooth rings are 23 and 24 held when the piston chamber 79 is supplied with sufficient pressure will. With the ring gear 22 held in place, the turbine 13 acts on the sun gear 32 the planetary gears 28 transmitted rotational movement that the smaller planetary gears 27 on the internal ring gear Roll 23 and impart a rotary movement over the arm star 21 of the shaft 15. This turning movement the shaft 15 is transmitted to the engine shaft, so that the rotatable parts of the engine are driven at a speed which is proportional to the speed of the turbine runner 36. During the operation of the engine, as before, the power ore is also generated by the planetary gears 38 42 driven, but at this point the power generator is relieved because it was on before switch, not shown, has been opened, so that the speed of the generator does not matter plays.

The regulating device 63 comprises a regulator arranged in the turbine inlet line 49 actuatable shut-off valve 82, as shown, for example, in British Patent 710 095 at 24 is. The valve 82 is from a solenoid or other electrical device can be actuated to put the turbine 13 in or out of operation. As I said above, it is Feed line 49 connected to a high pressure stage of the associated engine. The feed line 49 can also have an automatically closing junction, not shown here, to which an external, z. B. mobile, pressure medium source can connect to the Start the engine.

When the supply line 49 is supplied in front of the valve 82 with compressed air, one of the line 49 branching line 84 pressurized to the pneumatic part of the control device 63 with To supply printing power. In the line 84, a pressure control valve 83 is switched on, which is in the pneumatic Part of the control device 63 maintains the desired constant pressure. The administration 84 leads to a selector valve 85 for the starting process. This selector valve has a piston valve 86, which is attached to a membrane 87, which is biased by a spring 88 to the right. from the line 84 branches off a further line 90, which leads to a second from the hollow shaft 42 via the Gear 65 driven speed sensing device 91 leads, which is similar to the speed controller 71, whose Regulator valve is normally open, however, so that air can escape from line 90 to the atmosphere can until the shaft 42 has reached a predetermined speed. In the branch line 90 is upstream of the speed sensing device 91 switched on a throttle 92, and leads in the flow direction behind this throttle a branch line 93 to a chamber 94 on the opposite side of the diaphragm from the spring 88 87. A line 84 a leads from the selector valve 85 to the piston chamber 79 of the brake 73.

When the chamber 94 is not under pressure, the spring 88 tends to hold the piston valve 86 in the position shown in the drawing. In this position, the pressure medium supplied via line 84 is supplied via line 84 α to piston chamber 79, and piston 80 is pressed to the right in the drawing in order to bring brake 73 into effect and to hold ring gear 22 in place. If the rotor 36 of the turbine 13 now rotates, the shaft 15 and thus also the rotor of the aircraft main engine are driven so that the engine can be started. At the same time, a rotary movement is also communicated to the power generator shaft 42; the power generator 12 is, however, as already said above, during the on. let the engine unloaded. The second speed sensing device 91 responds to the rotational movement of the shaft 42 and is set such that it prevents air from escaping from the line 90 when the shaft 15 is rotated at a speed sufficient to start the drive train, which has the consequence that the chamber 94 is pressurized. This causes the membrane

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87 against the force of the spring 88 to the left, planet gears 26, 38 and the sun gear 40 move the shaft moves away and the piston valve 86 from its drawn 42 of the power generator. The idle friction of the neten position out to the left in a second position. The engine uses the shaft 15 to dem • treatment takes along, in which a turning of the arm star 21 away from the line 84 diverges a resistance Line 95 with the speed controller 71 in FIG. 5. The power generator can be connected in this way stands to be driven when the electrical equipment is at

The piston valve 86 has a recess 86 α, the engine at a standstill can be checked on the ground

about which in this second position, in which one should. The speed controller 71 works normally,

Connection between the line 95 and the rotation to the speed of the turbine 13 and thus also

number sensor 71 consists, the piston chamber 79 of the io that of the power generator 12 during a sol-

Brake 73 is vented to release brake 73. to control a constant speed test.

This process is played out by the closing of the It should be noted that shafts 15 and 33 as well

Regulator valve in the speed sensor 91 automatically, the differential gear 14 contribute to shocks

if the engine is to be dismantled and damped with a starting system that is compatible with the application of the

revolving speed. 15 energy required to start the jet engine

If the piston valve 86 could occur its described gie.

assumes the second position, that is, it is moved in such a way that the in F i g. 2 illustrates modified changes Speed controller 71 performs its regulating function, the order is similar to that according to FIG. 1 largely, If a spring-loaded processor occurs, the control device operates the lock-out element here 96 in action that prevents »ο Hch pneumatic. The arrangement of the shut-off valve From this position the piston valve 86 moves into the inlet line 49 of the turbine and that of can move out, even if the line 49 branching line 84 with the the pressure in the chamber 94 is lost, ζ. B. there- pressure regulator 83 to the selector valve 85, the structure by that the engine comes to a standstill. the selector valve and its control by the rotary

A throttle 97 is switched into the line 95, the number sensor 91 and the actuation of the brake 73 and behind this throttle in the direction of flow are as in the control device of FIG , which leads via the selector valve 85 direction 70 for the adjustment of the guide vanes 57 to the controller 71, from the line 84 via in connection. The speed controller 71 changes the one throttle 97 supplied with compressed air.
Amount of the air from the line 95 into the atmosphere 30 The turbine 102, here as two-stage Axialentweicfienden. As a result, the control turbine is shown, has a ring-shaped slide valve of the device 70 loading pneumatic laßverteilerleitung 103 and an outlet channel 101. Pressure is changed, which in turn controls the hydraulic Ausittsdüse.mit verder guide vanes 57 of the turbine, designated as a whole by 104. 35 adjustable passage cross-section. This

When the aircraft engine is started, the nozzle has a swiveling throttle body 105, should, a starter selector switch, not shown, is activated for a short time - the movements of which are timed after the fluid operated to a pressure with the lock 96 in a chamber 106 on the rear side connected electromagnet 100 to supply current, so that the amount of the channel 101 pass, which releases this so that the spring 88 can be changed to the piston 40 generating fluid. on Slide 86 back into the starting position shown - in this way, the pressure on the outlet side can push. When the turbine 13 is supplied with compressed air to the turbine 102 and thus also the turbine is rotated is, the brake 73 will change to effect number.

brought, and the energy supplied by the turbine so that the chamber 106 is used under one in the manner described on the shaft 15 45 variable pressure fluid to be transmitted. When the engine can turn its starter, this chamber is via a duct 107 number has reached and the speed sensor 91 is connected to the outlet port 101 in the. To the pressure described manner works to increase or decrease the selector valve 85 in the chamber 106, to adjust automatically and to release the brake is a branching off from this channel 107, for the switch for loading the current 50 atmosphere leading blow-off opening 108 can be provided, Actuate generator 12, whereupon the invention is controlled by a valve 110. The valve A suitable arrangement for regulating a constant 110 is determined by the controller 71 via the actuating speed of the power generator in the normal way ar- ting device 109 of the valve leading line works. As long as the power generator is controlled with the required 95.

Lent speed is driven, the piston 55 The nozzle 104 and the throttle slide provided in it 86 of the selector valve 85 through the air pressure body 105 are set so that the verin the turbine the chamber 94 in its the conduit 95 with the letting fluid in the form of a jet of speed regulator 71 connecting position, so occurs, which acts on the ambient air to the that the controller 71 works even when the aircraft engine by the development of a too-solenoid winding 100 to support unintentional or deliberate propulsive force. To this electricity is clearly being supplied. Way is the residual energy that is in that of the turbine

If one contains air when the engine is at a standstill without supplied and again exiting pressure actuation of the starter selector switch and thus releasing air, is made usable,
The lock 96 of the turbine 13 leads to compressed air. Both control devices described have the power generator 65, a safety device that operates the turbo generator 12 by means of the turbine. The turbine rotor 36 drives bine interrupted when the power generator or the turbine then passes through the sun gear 32 and the planetary gears. For this purpose, both 28, 27 have the ring gear 22 and this via the control devices a third through the power generation

Gerwelle 42 driven speed sensor 111 is provided, which is connected via a line 112 to the actuating device for the shut-off valve 82. A branch line is also connected 113 to the line 112, which leads to an arranged inside the turbine shaft 33 known device 114 for sensing overspeeding. Such a device 114 is proposed in patent 1,161,142, for example.

As soon as the speed of the power generator 12 or the turbine 13 or 102 increases beyond a value specified by the speed sensor 111 or 114 , the relevant speed sensor comes into action to vent the line 112 to the atmosphere, whereupon the shut-off valve 82 closes so that the supply of the working medium to the turbine is interrupted.

Claims (7)

Patent claims: 1. Gas turbine or other internal combustion engine engine system for aircraft with at least one auxiliary device which is driven via a differential epicyclic gearbox via which the engine's cranking motor also comes into effect, characterized in that of the three outwardly leading members (21, 32, 23) of the differential epicyclic gear (14 A) the first (21) is in constant drive connection with the engine (via 15), the second (32) with the torque motor (13) and the third (23 via 14 B) with the auxiliary device (12) and that the rotatability of a gear member (23) between the first (21) and the second (32) outwardly leading member about its own axis can be blocked by means of a retaining device (73), the retaining device (73) being controlled by a device responsive to the speed ( 91) is held in the locked position as long as the engine speed is below a predetermined value. 2. Internal combustion engine plant according to claim 1, characterized in that the with the auxiliary device (12) standing in constant drive connection member (23) with the input member (24) of a second epicyclic gear (14 B) is firmly connected, the second outwardly leading member ( 21) is also in drive connection with the engine (via 15) and its third outwardly leading member (40) with the auxiliary device (12), the device (91) responsive to the speed of the third member (40) this second epicyclic gear is driven. 3. Internal combustion engine power plant according to claim 2, characterized in that the links (21) of both epicyclic gears (14 Λ, 14Β) connected to the engine (via 15) each form the web in these. 4. Internal combustion engine power plant according to claim 1 to 3, characterized in that the starting motor (13) is a motor with continuously variable speed and its speed controlled by a constant speed controller (71) responsive to the speed of the auxiliary device (12) will. 5. Internal combustion engine power plant according to claim 4, characterized in that an air turbine is used as the starting motor (13), as is known per se for auxiliary drives, the speed of which can be regulated by changing the position of a throttle element (57, 105) which determines the air flow. 6. Internal combustion engine power plant according to claim 5, characterized by a shut-off valve (82) which is actuated by a speed sensor (114 or 111) responding to overspeed of the air turbine (13) or the auxiliary device (12) in order to increase the air flow rate of the air turbine (13 ) if an overspeed is detected. 7. Internal combustion engine power plant according to claim 1 to 6, characterized by a selection device (100) by means of which the retaining device (73) is to be brought into effect. 1 sheet of drawings