Turbine engine with a two-stage compressor

Abstract

Turbine engine with a two-stage compressor which is provided with a starter-generator (29) having a stator (6) and a rotor (7) disposed in the wheel of an axiai compressor (32), and further the turbine engine (31) is provided with a fuel pump (3) disposed in the inlet section of the turbine engine (31), wherein supply wires of the starter-generator (29) and the fuel pump (3) are led through a support rib (9) of the inlet section of the engine, and the turbine engine (31) is further provided with a slot (13) for air intake and cooling of the turbine bearing (22) arranged downstream of the radial compressor (33), and further the turbine engine (31) is provided with perpendicularly to the slot (13) and in the direction to the turbine section (25) continuing longitudinal channel (14) arranged concentrically with the shaft (19) between a carrier (34) of the turbine bearing (22) and the shaft (19), and further with continuing channels (16) in the carrier (34) for supplying cooling air to the turbine bearing (22), wherein the turbine bearing (22) is provided with a nozzle (17) for supplying fuel for lubrication and cooling and the compressor bearing (23) Is provided with a nozzle (11) for supplying fuel for lubrication and cooling, wherein the hollow shaft (19) is provided at its end in the turbine section (25) with bores (18) for conveying the air-fuel mixture from the bearing (22) into the hollow shaft (19) and at its other end in the compressor section (24) is provided with bores (20) for conveying the air-fuel mixture to the suction of the radial compressor (33) wheel and back to the combustion chamber (26).

Description

[0001] Turbine engine with a two-stage compressor

[0002] Technical field

[0003] The invention relates to a single-shaft turbine engine with a two-stage compressor.

[0004] State of the art

[0005] For jet or turbine engines that contain radial or diagonal compressors, it is necessary for starting the jet or turbine engines to ensure that the rotor is initially spun up to desired revolutions. A considerable number of technical solutions are known to enable the initial spin-up of turbine or jet engine rotors.

[0006] Solutions are known which take advantage of the effects of the compressed gas injected by the nozzle onto compressor blades. Solutions are also known which exploit the effects of a pyropattern on turbine blades, the rotational motion of which is transmitted by a common shaft with the compressor to the compressor impeller. It is also known to use a separate electric motor of the commutator type, which forms an electric starter and is mechanically coupled to the shaft of a jet or turbine engine, for example by means of a gearbox or a starting or idler clutch. If the electric motor is permanently coupled to the shaft of a turbine or jet engine by the means described above, it can also be used as a source of electrical power if suitably designed. Designs are also known which include a separate electric motor and a separate electric generator.

[0007] The disadvantage of the existing solutions is their high weight and high space requirements. Another disadvantage is also the relatively complex design of the known solutions and therefore the demanding production and the corresponding costs of the equipment.

[0008] CZ12724U1 discloses a jet or turbine engine, wherein a rotor of the synchronous electric motor is fixedly mounted on a rotatable portion of the jet or turbine engine coupled to a compressor, and wherein the stator of the synchronous electric motor is coaxial with the rotor of the synchronous electric motor and is mounted on a fixed part of the jet or turbine engine and is coupled to a power source and / or power consumer.

[0009] The starter-generator is usually located in front of the compressor impeller and is mechanically connected by a clutch to the engine rotor. It is usually a DC motor mounted on Its own bearings. The starter-generator therefore increases the overall length of the motor. The fuel pump is usually located on the outer casing of the engine. In the case of a compact engine design, it is not possible to place the pump on the engine casing without overlapping the outer casing.

[0010] The bearings of a turbine engine are lubricated by fuel injected into the bearings. Subsequently, the fuel-air mixture is discharged from the bearing space behind the turbine impeller, where the fuel is no longer ignited. The energy contained in the fuel is not used for turbine operation and the unburned fuel increases emissions.

[0011] The aim of the invention is to present a turbine engine with an efficient location of the starter-generator and fuel pump and with bearing lubrication that better utilizes the energy in the fuel.

[0012] Summary of the invention

[0013] The above-mentioned deficiencies are eliminated by the turbine engine with a two- stage compressor according to the invention, according to the characterizing part of claim 1.

[0014] Brief description of drawings

[0015] The invention will now be explained with reference to the drawings, in which Fig. 1 is a schematic section of a turbine engine according to the invention showing its components and Fig. 2 is a schematic section of a turbine engine showing the air and fuel flow.

[0016] Preferred embodiment of the invention

[0017] Fig. 1 is a schematic section of a turbine engine 31 according to the invention. The turbine engine 31 comprises a compressor section 24 and a turbine section 25, between which in the compressed gas path a combustion chamber 26 is inserted into which fuel nozzles (not shown) are arranged at a place 27. The compressor section 24 comprises a radial compressor wheel 33 with blades 10, while the turbine section 25 comprises a turbine impeller 28. In the embodiment shown, an impeller of axial compressor 32 is provided in which a rotor 7 of a starter-generator 29 is integrated. With the rotor 7 is coaxially arranged a stator 6 of the BLDC starter-generator, which is a three-phase synchronous generator excited by permanent magnets. This arrangement does not require bearings. At the same time, the rotor 7 is intensively cooled by heat dissipation to the blades 8 of the axial compressor 32. The electrical connection is made in such a way that the wires of the startergenerator 29 and the fuel pump 3 are guided through the rib 9 of the inlet section of the turbine engine 31. The above solution simplifies presented design of the starter-generator 29. The rotor of the starter-generator 29 consists of the body of the axial compressor 32 of the turbine engine 31 . Another advantage is shortening of the engine length and elimination of the need for an external starter-generator.

[0018] An electric fuel pump 3 is arranged in the inlet section of the turbine engine 31. The fuel pump 3 is driven by a BLDC motor 30 with a stator 2 and a rotor 1, The fuel inlet and outlet is provided by bores in the ribs 5 in the inlet section of the engine through a tube 4. The above solution eliminates the need to install the fuel pump on the engine casing, and thereby reducing the cross-sectional area of the turbine engine 31.

[0019] The hollow shaft 19 of the radial compressor 33 and the turbine is mounted in the rolling bearings 22, 23. The bearing 23 of the compressor 33 is lubricated by a nozzle 11. The bearing 23 is provided with a seal 12, which ensures that the fuel-air mixture is sucked out of the space of bearing 23 of the compressor by a vacuum in front of the inducer of radial compressor 33. For cooling the bearing 22, air taken through a slot 13 placed downstream of the radial compressor is used. A longitudinal channel 14 is arranged concentrically with the shaft 19 between the bearing carrier 34 of the bearing 22 and the shaft 19, which brings air to the bearing carrier 34 of the bearing 22 with the channels 16. The channel 14 is provided with a seal 15 to ensure that air enters the space with the lubrication nozzle 17. The bearing 22 is provided with a further seal 21 , which ensures that the fuel-air mixture is sucked from the space of the bearing 23 by a vacuum in front of the inducer of the radial compressor 33, where it is led by means of the bores 18 and 20. The shaft 19 is provided with a bore 18 at its end in the turbine section 25 of the turbine engine 31 , and is used to discharge the air-fuel mixture from the bearing 22 into the hollow shaft 19, and at the other end of the shaft 19 in the compressor section 24 of the turbine engine 31 the bore 20 is provided, and it is used to discharge the fuel-air mixture back into the intake of the radial compressor 33. Thus, the hollow shaft 19 is used for conducting the return fuel used for lubricating and cooling the turbine bearing 22 of the turbine engine 31.

[0020] Fig. 2 is a schematic cross-section of a turbine engine 31 showing the flow of air and fuel to lubricate and cool the bearings 22, 23. The air first passes through a slot 13 for taking air to cool the turbine bearing 22. The air then passes through channel 14 into channels 16 of bearing carrier 34 of turbine bearing 22 for supplying cooling air to turbine bearing 22 and then into space of the nozzle 17. The fuel-air mixture passes through bearing 22 and returns through bore 18 to the hollow shaft 19. The fuel is returned by this arrangement through the bore 20 to the combustion cycle of the turbine engine 31 , that is specifically to the suction of radial compressor 33, and further to the combustion chamber 26 of the turbine engine 31. The presented solution decreases fuel combustion and positively decreases proportion of unburned hydrocarbons in the exhaust gases.

[0021] List of reference signs:

[0022] 1 Rotor of BLDC motor of fuel pump

[0023] 2 Stator of BLDC motor of fuel pump

[0024] 3 Fuel pump

[0025] 4 Fuel inlet and outlet tube

[0026] 5 Ribs of inlet section for fuel inlet and outlet from the pump

[0027] 6 Stator of BLDC starter-generator

[0028] 7 Rotor of BLDC starter-generator

[0029] 8 Axial compressor wheel blades

[0030] 9 Rib for BLDC motors of fuel pump and starter-generator wires

[0031] 10 Radial compressor wheel blades

[0032] 11 Compressor bearing lubrication nozzle

[0033] 12 Compressor bearing seal

[0034] 13 Slot

[0035] 14 Longitudinal channel

[0036] 15 Shaft seal

[0037] 16 Channels in the bearing carrier

[0038] 17 Turbine bearing lubrication nozzle

[0039] 18 Bores

[0040] 19 Hollow shaft

[0041] 20 Bores

[0042] 21 Turbine bearing seal

[0043] 22 Turbine bearing

[0044] 23 Compressor bearing

[0045] 24 Compressor section of the motor

[0046] 25 Turbine section of the motor

[0047] 26 Combustion chamber

[0048] 27 Space for fuel nozzles

[0049] 28 Turbine impeller Starter-generator Motor of fuel pump Turbine engine Axial compressor Radial compressor Bearing carrier

Claims

Claims1. Turbine engine with a two-stage compressor having a compressor section and a turbine section, comprising a hollow shaft carrying a turbine bearing and a compressor bearing, characterized in that it is provided with a starter-generator (29) having a stator (6) and a rotor (7) disposed in the wheel of an axial compressor (32), and further the turbine engine (31) is provided with a fue! pump (3) disposed in the inlet section of the turbine engine (31), wherein supply wires of the starter-generator (29) and the fuel pump (3) are guided through a support rib (9) of the inlet section of the engine, and the turbine engine (31) is further provided with a slot (13) for air intake and cooling of the turbine bearing (22) arranged downstream of the radial compressor (33), and further the turbine engine (31) is provided with perpendicularly to the slot (13) and in the direction to the turbine section (25) continuing longitudinal channel (14) arranged concentrically with the shaft (19) between a carrier (34) of the turbine bearing (22) and the shaft (19), and further with continuing channels (16) in the carrier (34) for supplying cooling air to the turbine bearing (22), wherein the turbine bearing (22) is provided with a nozzle (17) for supplying fuel for lubrication and cooling and the compressor bearing (23) is provided with a nozzle (11) for supplying fuel for lubrication and cooling, wherein the hollow shaft (19) is provided at its end in the turbine section (25) with bores (18) for conveying the air-fuel mixture from the bearing (22) into the hollow shaft (19) and at its other end in the compressor section (24) is provided with bores (20) for conveying the air-fuel mixture to the suction of the radial compressor (33) wheel and back to the combustion chamber (26).

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