Method of auxiliary power takeoff from jet turbine engine of aircraft, and jet turbine engine suitable for implementation of such method

FIELD: engines and pumps.

SUBSTANCE: auxiliary power is taken off by means of shaft brought into action by means of high pressure turbine, and low pressure turbine efficiency is reduced at idle operation so that possibility of high pressure turbine operation at the speed that is sufficient for supply of the required auxiliary power can be provided.

EFFECT: invention allows optimum redistribution of powers of low and high pressure turbines.

4 cl, 2 dwg

 

The invention relates to the creation of auxiliary power required for equipment on Board the aircraft, with the power taken from the turbojet engine(s) of the aircraft.

In modern aircraft needs in electrical energy more and more increase. Using increasingly powerful generators of electricity. Such a generator of electricity to operate through the turbojet engine of the aircraft (for example, EP 1617053, 18.01.2006). Known for the selection of the required mechanical power from the shaft, which is connected with the high-pressure turbine. More precisely, the radial shaft mechanically connected to the axial shaft connected to the high-pressure turbine, and the power down to the gearbox, which drives the electricity generator. If you want a lot of power, this solution leads to difficulties when the engine is idling, if it's on the ground or in flight, due to the high level of torque required to actuate electricity generator. This torque leads to the work of the high-pressure turbine in an undesirable operating range.

The invention attempts to improve this known system, taking into account modern requirements for auxiliary power and taking into account the new levels of torque which should be transferred without affecting the operation of the turbine high pressure when idling.

The idea on which the invention is based, is that at idle to reduce the efficiency of the low-pressure turbine located further downstream from the high-pressure turbine to provide the possibility of increasing the speed of rotation of the turbine high pressure (up to a level that allows you to take it from a higher power) without increasing the thrust of the engine, since this increase is undesirable during the stages of operation of the engine at idle.

More precisely, the invention results from the method of selection of the auxiliary power from the turbojet engine of the plane containing from near-stream side to the far downstream side: high-pressure turbine, low pressure turbine, the method is a method of this type, which consists in the selection of power through the shaft driven by the high-pressure turbine, and is characterized in the mode of idle running of lowering the efficiency of the low-pressure turbine thus, to ensure that high-pressure turbine at a speed which is sufficient to supply the required auxiliary power.

Therefore, the efficiency of the low-pressure turbine is reduced to cause her samadhan the e rotation and provide more rapid rotation of the turbine high pressure.

The efficiency of the low-pressure turbine can be lowered under the influence of radial clearance on the moving blades of the turbine.

It should be noted that the change in radial clearance of the moving blades is a well-known by itself, the way [using control control type axial gap of the low-pressure turbine (LPTACC)], but it involves a different use.

According to another distinctive feature, which is preferred, lowering the efficiency of the low-pressure turbine may be provided by exposure step of blades, nozzle Assembly of the apparatus, at least some of the turbine stages. System variable pitch vane nozzle apparatus low-pressure turbine is used to change the rotation speed of the turbine (which can be seen as lowering its efficiency). You can combine both of these tools.

The engine computer provides the ability to change these parameters as a function of motor speed and needs in electrical energy. Thus, it is possible to avoid the increase of thrust of the engine (through the use of controlled losses efficiency low-pressure turbine), while maintaining the ability to keep pace with the high-pressure turbine at such a level that, in spite of considerable value taken from her power, the working point of the tour the ins high pressure remains above the critical value.

According to a preferential distinctive sign of the change in efficiency of the low-pressure turbine is performed with the servo for measuring torque transmitted by a (conventional) mechanical transmission system located between the shaft driven by the high-pressure turbine, and a generator of electricity.

The invention also offers a turbojet engine of the plane that contains the near-stream side to the far downstream side of the high-pressure turbine and low pressure turbine, a shaft driven by the high-pressure turbine and gear reduction system connected with the shaft for selection from his power, with a turbojet engine differs in that it includes means for changing the efficiency of the low-pressure turbine and controls to manage changes in efficiency, and control means controlled by the sensor transmitting a signal characterizing quantity consumed by auxiliary power.

Mechanical transmission system (among other parts) actuates one or more generators of electricity.

Means changes the cap may include a system for controlling the radial clearance of the movable blades of the low-pressure turbine and/or the system on which I pitch control of the blades of the nozzle apparatus of the low-pressure turbine.

Preferably, the means changes the cap contained a computer, responsive to the torque sensor, by itself, associated with mechanical transmission system located between the shaft driven by the high-pressure turbine, and a generator of electricity.

The invention will be better understood and its other advantages will be more apparent in the light of the following description, given only as an example and made with reference to the accompanying figures, in which

figure 1 presents a schematic view in section of a turbojet aircraft engine, suitable for the selection of auxiliary power according to the invention;

figure 2 presents a view similar to the view of figure 1 and showing a variant embodiment of the invention.

Two variants of the design, schematically shown respectively in figures 1 and 2 can be combined by providing a computer suitable for controlling the two systems that need to change the efficiency of the low-pressure turbine.

Turbofan engine 11 shown in figure 1, with the near-stream side to the far downstream side has traditionally been the fan 13, 15 compressor low pressure compressor 17 high-pressure chamber 19 of the combustion turbine 21 of the high pressure turbine 23 low pressure. T is rbine 23 low pressure mechanically connected to the axial shaft 25, operate as the fan 13 and the compressor 15 to the low pressure. Turbine 21 high pressure is connected to the axial shaft 27, which action, in particular, the compressor 17 high pressure. This Assembly is called the cascade high pressure. The shaft 27 is mechanically connected to the mechanical transmission system 29 having radial shaft 31, operate the generator 33 of electricity through the appropriate gear.

Currently, the generator 33 of electricity to provide the power required onboard equipment and all the equipment in the passenger cabin must be a generator of high power, therefore requiring torque transfer great value by means of radial shaft 31.

In this example, the torque is measured by a sensor 37, associated with radial shaft 31. The torque sensor signals characterizing the torque transmitted radial shaft 31, and hence the power extracted from the turbine 21 high pressure. This signal is fed to the input of the computer 40, applicable to control at least one structural parameter of the low-pressure turbine. More precisely, this parameter represents one of the parameters, which provides the ability to change (reduce) the efficiency of the turbine low pressure which I thus, that high pressure turbine can operate with sufficient speed when the engine is idling. Thus the required auxiliary power can be selected without high pressure turbine worked in an undesirable working environment.

In the example shown in figure 1, the computer 40A performs the control function of the radial clearance of the movable blades of the low-pressure turbine. Control output 42 of the computer acts on the system 44 (known in itself) to control the radial clearance low-pressure turbine. This management system gap is a system type LPTACC; there are other instances of its application. If the radial clearance of blades increases, the efficiency of the turbine low pressure will be lowered, while providing the possibility of working cascade high pressure above its critical speed without having to pull from the fan 13 has become incompatible with the idle speed.

In the example shown in figure 2, the overall layout is the same and again will not be described. However, the computer now 40b is designed to perform the function of the control variable pitch blades 45 nozzle apparatus of the turbine 23 of the low pressure. Therefore, the nozzle vanes of the apparatus of this turbine is consistent with the system 47 pitch change, which result in D. the op perate outside of the casing 49.

Of course, as mentioned above, the computer may perform both of the above functions of management, namely management of radial clearance of moving blades and control of variable pitch blades, nozzle Assembly of the device.

The signal from sensor 37 of torque, is a characteristic of the auxiliary power extracted from the generator 33 of electricity. As a result, the signal from sensor 37 will be transmitted to the computer, which takes a decision in respect of the degree to which should be "degraded" efficiency of the turbine 23 of the low pressure to ensure that the work of the cascade high pressure could be maintained at a sufficient level when the engine is idling, without the development of the fan 13 this thrust, which is becoming incompatible with the proper idling.

1. The method of selection of the auxiliary power from the turbojet engine of the plane that contains the near-stream side to the far downstream side of the turbine (21) high pressure turbine (23) low pressure, and the PTO is realized by means of the shaft (27), driven by the high-pressure turbine, wherein in a mode of idling through appropriate management can reduce the efficiency of the turbine (23) low pressure through effects on RA the territorial gap (44) movable blades of the low-pressure turbine and/or by altering the step (47) blades nozzle apparatus the low-pressure turbine to facilitate operation of the turbine (21) high pressure at a rate sufficient to supply the required auxiliary power.

2. The method according to claim 1, characterized in that the change in the efficiency of the low-pressure turbine is performed with servocontrolled to measure (37) of torque transmitted mechanical transmission system (29)located between the shaft driven by the high-pressure turbine, and a generator (33) of electricity.

3. Turbojet aircraft with near-stream side to the far downstream side of the turbine (21) high pressure turbine (23) low-pressure shaft (27), driven by the high-pressure turbine and gear reduction system (29)connected with the shaft for selection from his power, characterized in that it includes means (44-47) to change the efficiency of the low-pressure turbine and means (40A-40b) to manage changes in efficiency, and control means controlled by a sensor (37)applying the signal characterizing quantity consumed by auxiliary power, with the means to change the cap contained a system for controlling the radial clearance (44) movable blades of the low-pressure turbine and/or the means to change the cap contain the system (47) for pitch control of the blades of the nozzle apparatus of the low-pressure turbine.

4. Turbojet, dvigatelya to claim 3, characterized in that the means for changing the cap contain computer (40A-40b), controlled by the sensor (37) of torque associated with mechanical transmission system located between the shaft driven by the high-pressure turbine, and a generator (33) of electricity.



 

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