CN207437204U

CN207437204U - Hybrid gas turbine

Info

Publication number: CN207437204U
Application number: CN201721102485.0U
Authority: CN
Inventors: 迟多功
Original assignee: Individual
Current assignee: Individual
Priority date: 2017-08-21
Filing date: 2017-08-21
Publication date: 2018-06-01
Anticipated expiration: 2027-08-21

Abstract

Hybrid gas turbine is made of rotor, cylinder barrel, burner noz(zle), compressor, bearing, fuel feed system, ignition system, gas-guide pipeline, exhaust system, startup motor etc., wherein rotor is by movable vane piece and turbine group and compression impellor is fixed together with main shaft and movable vane piece is parallel to main-shaft axis, rotor equipped with multiple row movable vane piece is corresponding with the multiple row burner noz(zle) installed on cylinder barrel barrel and is set in together and forms hybrid gas turbine so that gas turbine proficiency more height output power bigger.When gas turbine works, the air and fuel of compression are sent to combustion chambers burn, high temperature and high pressure gas after burning spray to impeller movable vane piece by nozzle lip, so as to which the external output mechanical energy of impeller high-speed rotation be promoted to drive other mechanical (such as generator) actings.

Description

Hybrid gas turbine

First, technical field

The present invention relates to a kind of gas turbines, and several row leaves are installed with more particularly to a kind of main shaft by gas turbine is parallel Wheel and the gas turbine formed with gas turbine main-shaft axis into certain angle of inclination and radially mounted turbine group.

2nd, background technology

Gas turbine used in present middle-size and small-size power plant and other occasions is essentially all the hot kinetic energy using combustion gas Propelling gas turbine engine rotor is converted into mechanical energy and drives electrical power generators, axially propelling gas turbine engine step by step during acting Rotor axis are into certain angle of inclination and radially mounted movable vane piece, so as to which rotor be driven to rotate, after finally doing work lack of gas from The other end discharge of cylinder.Since there is movable vane piece angle of inclination always unavoidably to generate axial force, this portion of energy, which does not generate, to be turned Away from and waste, and the remaining kinetic energies of lack of gas could not be utilized further after doing work.

3rd, the content of the invention

It is an object of the invention to provide a kind of main shaft by gas turbine it is parallel be installed with several row impellers and with combustion gas wheel The more efficient hybrid gas turbine that machine main-shaft axis is formed into certain angle of inclination and radially mounted turbine group.

In order to achieve the above objectives, present invention offer is a kind of makes the thrust that combustion gas generates along gas turbine rotor outer rim and hangs down The combination that rotor generates the positive-pressure type gas turbine and turbine type gas turbine of the pure moment of couple directly is acted in rotor axis, from And the hybrid gas turbine that the hot kinetic energy completion for foring combustion gas is done work twice.

The gas turbine is by main shaft, cylinder barrel, movable vane piece, turbine group, burner noz(zle), compressor, bearing, fuel supply system The compositions such as system, igniter, gas-guide pipeline, exhaust system, starter motor, described main shaft one end are coaxially coupled compressor compression impellor And the other end coaxially fixed movable vane piece (or impeller) and turbine group and makes turbine be assembled in the exhaust side of main shaft so as to constitute The rotor of hybrid gas turbine can be integrally fixed on two impeller side plates with the fixed movable vane piece of main shaft and form several row leaves Wheel can also be linear leaf and the fixed structure of main shaft；Axially disposed several row are circumferentially installed on the barrel of the cylinder barrel Multiple inclined burner noz(zle)s form nozzle stage and corresponding with impeller grade, should also make the orientation angle of burner noz(zle) lip with The movable vane piece of impeller is adapted, and the burner noz(zle) installed on these cylinder barrel barrels is connected by the gas outlet of gas-guide pipeline and compressor Lead to and be connected with igniter and fuel feed system and form many combustion chambers；The coaxial fixed connection in one end compressor Coaxially fixed movable vane piece and turbine group and turbine are assembled in the exhaust side of main shaft and pass through bearing branch for compression impellor and the other end It supports main shaft on base plate and is fixedly supported on by bearing on base plate and one end is linked with compressor outer cylinder and another One end is set in together with the cylinder barrel that exhaust system end cap is linked and makes its nozzle level position corresponding with impeller level position.

When gas turbine works, main shaft rotation is driven by starter motor, is drawn air into simultaneously by the compressor being mounted on main shaft Compression, compressed air are sent through air leading-in conduit to burner noz(zle), into the air of burner noz(zle) and by fuel feed system It is lighted after being pumped into the fuel mixing come by igniter, the high temperature and high pressure gas after burning spray to movable vane piece (one by nozzle lip Secondary acting) it is complete after blow to turbine group (twice work doing) again, so as to which the external output mechanical energy of main shaft high-speed rotation be promoted to drive other Mechanical (such as generator) acting so completes gas turbine by " air-breathing calms the anger, burns, does work " Four processes.When combustion gas wheel Starter motor disengages automatically when machine impeller reaches certain speed, and gas turbine voluntarily works.

4th, illustrate

Fig. 1 is a kind of longitudinal sectional view of embodiment of the present invention.

Fig. 2 is Fig. 1 along the sectional view at A-A.

Fig. 3 is the outside drawing of the first embodiment of the present invention.

Fig. 4 is Fig. 3 along the sectional view at B-B.

Fig. 5 is the longitudinal sectional view of another embodiment of the present invention.

Fig. 6 is Fig. 5 along the sectional view at C-C.

5th, specific embodiment

Specific embodiment is described in detail below in conjunction with the accompanying drawings.

Fig. 1, Fig. 2, Fig. 3, a kind of hybrid gas turbine shown in Fig. 4.As shown in the figure the gas turbine by starter motor 1, Compressor 2, cylinder barrel 11, vent line 3, fuel feed system 4, impeller 5, turbine group 6, main shaft 13, exhaust system 9, bearing 7, Bearing spider 8, exhaust bearing 10, base plate 12, compressor bearing 14, starter motor bearing 15, shaft coupling 16 and 17, burner noz(zle) 18th, the compositions such as igniter (being not drawn into figure), shown impeller 5 (see Fig. 4) are made of impeller side plate 19, movable vane piece 20, movable vane piece 20 annulars are fixed at two impeller side plates, 19 outer rim for being provided with venthole and constitute impeller 5 with 13 centerline parallel of main shaft；It is several The compression impellor of row impeller 5 and several groups of turbines 6 and compressor 2 is concentrically fitted on main shaft 13 and turbine group 6 is made to be mounted in main shaft 13 exhaust side forms the rotor of gas turbine, and main shaft 13 is rotatably supported in basis by two bearings 7 and two bearings bearing 8 On plate 12 and by shaft coupling 16 and 17 13 one end of main shaft is made to be connected with starter motor 1 and the other end and output machinery such as generator (being to draw in figure) connection；The cylinder barrel 11 is cylinder type cylinder body, and circumference opens many inclined holes on barrel, these inclinations Hole be adapted at the angle of inclination in axial arranged several row and hole and direction with the movable vane piece 20 on main shaft 13, cylinder barrel 11 1 End and 2 shell of compressor are fixed and the exhaust end cover fixed connection of the other end and exhaust system 9 and with being vented bearing 10 and calm the anger Bearing 14 is fixedly supported on base plate 12, arranged on 11 circumference of cylinder barrel in inclined hole be fixedly mounted burner noz(zle) 18 and The movable vane piece of the lip and main shaft that make vent line 3, fuel feed system 4, igniter coupled logical and make burner noz(zle) 18 20 are adapted；Be rotatably supported in by bearing 7 and bearing spider 8 on base plate 12 and it is fixed by be filled with turbine group 6, impeller 5, The main shaft 13 of 2 compression impellor of compressor is with being fixedly supported on base plate 12 and being connected firmly with exhaust bearing 10 and bearing 14 of calming the anger The calm the anger cylinder barrel 11 of 9 exhaust end cover of shell and exhaust system of compressor 2 is concentrically set with together and makes several row leaves on main shaft 13 Wheel 5 is corresponding with several 18 positions of row burner noz(zle) on 11 wall of cylinder barrel, should also make the orientation angle of 18 lip of burner noz(zle) It is adapted with the movable vane piece 20 of impeller 5；Simultaneously unicom between 2 shell of compressor of vent line 3 and cylinder barrel 11 with sealing every It opens, also needs to be separated with sealing between the end cap of exhaust system 9 and main shaft 13, and the exhaust outlet of 9 exhaust end cover of exhaust system can Access secondary use is discharged into air.

During work, by starter motor 1 main shaft 13 is driven to rotate, drawn air into and pressed by the compressor 2 being mounted on main shaft 13 Contracting, compressed air are sent through vent line 3 to burner noz(zle) 18, into the air of burner noz(zle) 18 and by fuel supply system System 4 is lighted after being pumped into the fuel mixing come by igniter, and the high temperature and high pressure gas after burning are sprayed by the lip of burner noz(zle) 18 To movable vane piece 20 (once do work) it is complete after blow to turbine group 6 (twice work doing) again, so as to promote 13 high-speed rotation of main shaft externally defeated Go out mechanical energy and drive other mechanical (such as generator) actings.Starter motor 1 is automatic when gas turbine main shaft 13 reaches certain speed It disengages, gas turbine voluntarily works.

The hybrid gas turbine of another kind shown in Fig. 5 and Fig. 6, Fig. 5 is the longitudinal sectional view of the gas turbine, and Fig. 6 is The axial section of magnification ratio is splitted at along C-C.The gas turbine is by starter motor 1, compressor 2, cylinder barrel 11, master as shown in the figure Axis 28, movable vane piece 24, turbine group 6, vent line 3, fuel feed system 4, exhaust system end cap 26, bearing 27 and 29, exhaust The groups such as bearing 10, base plate 12, compressor bearing 14, shaft coupling 16 and 17, burner noz(zle) 18, igniter (being not drawn into figure) Together with being installed in into one end of, the main shaft 28 with the compression impellor fixation of compressor 2 and the other end of main shaft 28 is coaxially fixed The many movable vane pieces 24 parallel with main-shaft axis and blade and main-shaft axis are installed into inclined turbine group 6 and make turbine group 6 Mounted in the exhaust side of main shaft 13, main shaft 28 be rotatably supported in by bearing 27 and 29 on base plate 12 and by shaft coupling 16 with 17 make 28 one end of main shaft be connected with starter motor 1 and the other end is connected with output machinery such as generator (in figure for draw)；The cylinder Cylinder 11 is cylinder type cylinder body, and circumference opens many inclined holes on barrel, these inclined holes in axial arranged several row simultaneously And hole angle of inclination and direction and movable vane piece 24 be adapted, 11 one end of cylinder barrel and the shell of compressor 2 are coaxial fixed and another End is supported on the 26 coaxial fixed connection of exhaust end cover of exhaust system and with the bearing 14 of calming the anger of bearing 10 is vented on base plate 12； Arranged on 11 circumference of cylinder barrel in inclined hole burner noz(zle) 18 is fixedly mounted and make vent line 3, fuel feed system 4, Igniter is coupled logical and makes the lip of burner noz(zle) 18 and 11 centerline parallel of cylinder barrel (optimum state)；By bearing 27 with 29 are supported on the shell of compressor 2 and exhaust end cover 26 and same with the compression impellor of compressor 2 and movable vane piece 24 and turbine group Together with the fixed main shaft 28 of axis is concentrically set with the cylinder barrel 11 being supported on base plate 12 and 18 lip of burner noz(zle) should be made Orientation angle is adapted with movable vane piece 24, while is separated between 2 shell of compressor and main shaft 28 with sealing, and exhaust end cover 26 Exhaust outlet can access secondary use or be discharged into air.

During work, by starter motor 1 main shaft 28 is driven to rotate, drawn air into and pressed by the compressor 2 being mounted on main shaft 28 Contracting, compressed air are sent through vent line 3 to burner noz(zle) 18, into the air of burner noz(zle) 18 and by fuel feed system It is lighted after the 4 fuel mixing being pumped by igniter, the high temperature and high pressure gas after burning are sprayed to by the lip of burner noz(zle) 18 Turbine group 6 (twice work doing) is blowed to again after movable vane piece 24 (once doing work) is complete, so as to which 28 high-speed rotation of main shaft be promoted externally to export Mechanical energy drives other mechanical (such as generator) actings.When gas turbine main shaft 28 reaches certain speed, starter motor 1 is automatic takes off It opens, gas turbine voluntarily works.

Claims

1. a kind of hybrid gas turbine, by main shaft (13,28), movable vane piece (20,24), turbine group (6), cylinder barrel (11), burning Nozzle (18), compressor (2), bearing (7,27/29), bearing (8,10/14), fuel feed system (4), igniter, gas-guide tube The compositions such as road (3), exhaust system (9,26), shaft coupling (16,17), starter motor (1), on the barrel of the cylinder barrel (11) vertically It arranges that several row are circumferentially installed with multiple inclined burner noz(zle)s (18) and form nozzle stage, is installed on cylinder barrel (11) barrel Burner noz(zle) (18) connected by gas-guide pipeline (3) with the gas outlet of compressor (2) and with igniter and fuel feed system (4) It is connected and forms many burner noz(zle)s (18)；It is formed together with movable vane piece (20,24) and turbine group (6) are connected firmly with main shaft (13) Gas turbine rotor and the multiple row that is circular layout on outer tube wall tilt burner noz(zle) and (18) and pass through bearing (8,10/14) It is fixedly supported on base plate (12) and one end is associated with compressor (2) outer cylinder and the other end and exhaust system (9,26) row The cylinder barrel (11) that gas end cap is linked concentrically is set in together and makes the orientation angle of burner noz(zle) (18) and the movable vane of rotor Piece (20,24) is adapted, and rotor is rotatably supported in by bearing (7,27/29) and bearing (8,10/14) on base plate (12), cylinder Cylinder (11) is fixedly supported on bearing (10,14) on base plate (12), is installed with the master of movable vane piece (20,24) and turbine group (6) The other end of axis (13) is associated with compressor (2) and the outlet of compressor (2) is connected with burner noz(zle) (18), and feature exists It is concentrically connected firmly with main shaft (13) in movable vane piece (20,24) and turbine group (6) and makes turbine group (6) mounted in main shaft (13,28) Exhaust side and the movable vane piece (20) on the main shaft should be made parallel with main shaft (13) axis and with cylinder barrel (11) barrel arrange with The position of the multiple row annular combustion nozzle (18) of cylinder barrel (11) centerline parallel is corresponding.

2. hybrid gas turbine according to claim 1, burner noz(zle) (18) be made cylinder type shell the upper end with Vent line (3), fuel feed system (4) and igniter connect and the flat lip connected with housing cavity and lip is made in lower end With cylinder barrel (11) centerline parallel.