CN208907369U - A kind of inner cooling system of 2 grades of turbine rotors of gas turbine - Google Patents

Abstract

A kind of inside cooling structure of 2 grades of turbine rotors of gas turbine, belongs to gas turbine structure field.The utility model is in order to solve the two stage turbine gas turbine rotor structures of existing not coaxial different rotating speeds, without a kind of applicable inside cooling structure problem.The utility model includes cooling air guiding device, first order turbine wheel disc, second level turbine wheel disc, turbine front end axis and turbine rear axle, turbine rear axle is arranged in the axis of turbine front end, turbine front end axis and the concentric arrangement of turbine rear axle, the circumferential direction of turbine front end axis is provided with level-one turbine wheel disc connection ring, the circumferential direction of turbine rear axle is provided with second level turbine wheel disc connection ring, first order turbine wheel disc is fixedly mounted in level-one turbine wheel disc connection ring, and second level turbine wheel disc is fixedly mounted in second level turbine wheel disc connection ring.The utility model maximizes the dosage for reducing high pressure cooling air, improves gas turbine proficiency, realizes the inner cooling system of not coaxial different rotating speeds turbine rotor.

Description

A kind of inner cooling system of 2 grades of turbine rotors of gas turbine

Technical field

The utility model relates to a kind of inner cooling systems of gas turbine, belong to gas turbine structure field.

Background technique

Currently, an effective ways for improving its cycle efficieny are the combustions for improving combustion gas turbine for gas turbine unit Gas inlet temperature, and improving one effective ways of initial temperature is exactly to pass through reasonable cooling air system to high-temperature component of gas turbine Design is cooled down and is protected to it, since the temperature that the high-temperature material that current turbine blade uses can bear is restricted, Therefore to the high-temperature component of gas turbine, especially turbine blade, it is necessary to take reliable cooling provision to reduce its work temperature Degree, to guarantee the operation of gas turbine safety, improve turbine working-blade cooling effect be development high efficiency combustion engine must So require.

For gas turbine, the gas turbine cooling system scheme inquired into patent has been delivered at present, both for passing through The monoblock type that the means such as bolt or welding are bound up coaxially with the turbine rotor of revolving speed the case where, however, for having Two stage turbine, and the turbine rotor of the gas turbine of the not coaxial different rotating speeds of two stage turbine, there are no in applicable turbine rotor Portion's cooling system scheme.

Utility model content

Purpose of the utility model is to solve existing different rotating speeds two stage turbine gas turbine rotor structures, without one The applicable inside cooling structure problem of kind, and then a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine is provided.

The technical solution of the utility model includes:

A kind of inside cooling structure of 2 grades of turbine rotors of gas turbine, including cooling air guiding device, first order turbine Wheel disc, second level turbine wheel disc, turbine front end axis and turbine rear axle, the turbine front end axis are hollow shaft, turbine rear end Axis is arranged in the axis of turbine front end, turbine front end axis and the concentric arrangement of turbine rear axle, the circumferential direction of the turbine front end axis It is provided with level-one turbine wheel disc connection ring, the circumferential direction of the turbine rear axle is provided with second level turbine wheel disc connection ring, and first Grade turbine wheel disc is fixedly mounted in level-one turbine wheel disc connection ring, and second level turbine wheel disc is fixedly mounted on second level turbine wheel disc In connection ring；

The cooling air guiding device is used to introduce the cooling air-flow of the gas turbine from compressor exhaust, cooling Air-deflector and first order turbine wheel disk form blade bottom chamber, before the two forms first order turbine wheel disc with shell again Chamber, the cooling air-flow from hiigh pressure stage bleed are largely passed through wheel disc rear chamber after flowing through first order turbine wheel disc front chamber, Small part from first order root of blade is passed through the after converging after blade bottom chamber with the cooling air-flow from compressor exhaust One grade blade；

It is equipped with stator blade inner ring between the first order turbine wheel disc and second level turbine wheel disc, is equipped in stator blade inner ring Spacer member, spacer member will be separated to form first order turbine wheel disc rear chamber between first order turbine wheel disc and second level turbine wheel disc With second level turbine wheel disc front chamber, cooling air-flow flows through first order turbine wheel disc rear chamber and second level turbine wheel disc ante-chamber Room cools down after cooling respective wheel disc side on rear side of first order root of blade respectively and after cooling second level root of blade again to second Grade blade gas supply.

Lower chamber between two-stage disk stage, turbine are formed at the first order turbine wheel disc and second level turbine wheel disc lower part Between centers circulation chamber is formed with turbine rear axle inside the axis of front end, lower chamber connects between centers circulation chamber and two-stage disk stage It is logical；

The second level turbine wheel disc connection ring that the second level turbine wheel disc and turbine rear axle is circumferentially arranged forms second level The installation place of turbine wheel disc lower part cooling chamber, the second level turbine wheel disc and second level turbine wheel disc connection ring radially processes There are multiple first through hole, forms second level turbine wheel disc rear chamber, stream between the second level turbine wheel disc and turbine cylinder body Through between two-stage disk stage lower chamber cooling air-flow flow into second level turbine wheel disc lower part cooling chamber, and by first through hole into It is cooled down on rear side of the root of blade of the second level after entering second level turbine wheel disc rear chamber.

Further, the upper end of the cooling air guiding device uses labyrinth gas seals structure and first order turbine wheel disc Top be coupled, the middle part of the lower part of cooling air guiding device and first order turbine wheel disc uses the first labyrinth seal knot Structure is coupled, and blade bottom chamber is formed on the top of cooling air guiding device and first order turbine wheel disc；The cooling The lower case of air-deflector is equipped with gas tight jacket, and gas tight jacket is cooperated using the second comb tooth sealing structure and turbine front end axis Installation, the gentle big envelope of cooling air guiding device, shell, first order turbine wheel disc form first order turbine wheel disc front chamber.

Further, the lower end for the spacer member installed in the stator blade inner ring uses third comb tooth sealing structure and first The lower end of grade turbine wheel disc is coupled.

Further, it is close that the 4th comb tooth sealing structure, the 5th comb teeth is respectively adopted in the left and right ends of the stator blade inner ring Seal structure is coupled with first order turbine wheel disc, second level turbine wheel disc.

Further, the between centers circulation chamber interior that the turbine rear axle and turbine front end axis are formed is equipped with air Pipe is introduced, between centers circulation chamber is separated to form compressor sub-high pressure grade tap air channel to air introduction and compressor low-pressure stage is drawn Gas channel is equipped with axle sleeve in the turbine rear axle, by the 6th comb tooth sealing structure between axle sleeve and turbine front end axis, Axial ring gap is formed between axle sleeve and second level turbine wheel pan bottom, compressor low-pressure stage tap air channel passes through the 6th comb teeth Lower chamber is connected between sealing structure and two-stage disk stage, meanwhile, compressor low-pressure stage tap air channel passes through axial ring gap Cooling chamber is connected to second level turbine wheel disc lower part.Further, between the turbine front end axis and first order turbine wheel disc Level-one turbine wheel pan bottom cooling chamber is formed, is radially machined with multiple second through-holes on the turbine front end axis, it is described Compressor sub-high pressure grade tap air channel is connected to by the second through-hole with level-one turbine wheel pan bottom cooling chamber, level-one turbine wheel disc Lower chamber is connected between bottom coohng chamber and two-stage disk stage.

Further, it is machined with multiple third through-holes in the axial direction of the cooling air guiding device, described first Grade turbine wheel disc top is machined with hole on multiple first order wheel discs, on third through-hole and the first order wheel disc hole respectively with blade bottom Chamber, the cooling air-flow of compressor exhaust is after the third through-hole of cooling air guiding device enters blade bottom chamber First order turbine rotor vane root of blade is passed through by hole on first order wheel disc and provides cooling air for first order movable vane；Described The middle position of level-one turbine wheel disc is machined with multiple fourth holes, and the first order turbine wheel disc front chamber passes through four-way Hole is connected to first order turbine wheel disc rear chamber.

Further, the top of the second level turbine wheel disc is machined with hole on multiple second level wheel discs, the second step cone Hole is connected to second level turbine wheel disc front chamber on disk, and the cooling air-flow into second level turbine wheel disc front chamber passes through the second level Hole is passed through second level turbine rotor vane root of blade and provides cooling air for second level movable vane on wheel disc.

Further, pass through the 7th comb tooth sealing structure cooperation peace between the second level turbine wheel disc and turbine cylinder body Dress, the cooling air-flow into second level turbine wheel disc rear chamber flow through cooling second level turbine rotor vane after the 7th comb tooth sealing structure On rear side of root of blade.

Further, the first order turbine wheel disc is connected by screw bolts mode and is fixedly mounted on level-one turbine wheel disc company It connects on ring, the second level turbine wheel disc is fixedly mounted in second level turbine wheel disc connection ring.

The utility model has the following beneficial effects: the utility model draws four strands of compressions skies from the different parts of compressor Gas flows into first order turbine wheel disc blade bottom by air-deflector as cooling air, a part of high-pressure compressor exhaust Chamber, predominantly first order turbine rotor vane provide cooling air；Bleed is arrived by the second comb tooth sealing structure between compressor hiigh pressure stage Up to first order turbine wheel disc front chamber, then after being passed through wheel disc by multiple fourth holes in the middle position of first order turbine wheel disc The first order turbine wheel disc rear chamber of side, main cooling first order turbine wheel disc two sides；Bleed between compressor low-pressure stage, by saturating The compressor low-pressure stage tap air channel of flat front end axis inside center between centers circulation chamber is passed through lower chamber between two-stage disk stage；Pressure Bleed between mechanism of qi sub-high pressure grade is passed through first order turbine wheel pan bottom, cooling wheel disc by compressor sub-high pressure grade tap air channel Behind bottom, converge with compressor low-pressure stage tap air channel air-flow, it is common to provide cooling air and cold for second level turbine wheel disc movable vane But second level turbine wheel disc two sides；Each stock air-flow is ultimately discharged into main blast tube after the cooling each structural plane of journey；

The cooling medium of the utility model uses the compressed air drawn from compressor, it then follows turbine high temperature and pressure position Cooling air is drawn from compressor high-pressure section, and the lower second level turbine wheel sections cooling air of temperature and pressure is mainly from pressure The principle that the low-pressure stage of mechanism of qi front is drawn maximizes the dosage for reducing high pressure cooling air, improves gas turbine proficiency, realizes The inner cooling system of not coaxial different rotating speeds turbine rotor, this system have cooling turbine rotor component, for cooling blade Gas supply, the effect for preventing combustion gas from flowing backward and obturaging.

Detailed description of the invention

Fig. 1 is gas turbine turbine rotor inner cooling system flow passage structure diagrammatic cross-section；

1- cooling air guiding device in figure, 2- third through-hole, 3- labyrinth gas seals structure, hole on 4- first order wheel disc, 5- First order turbine wheel disc, the 4th comb tooth sealing structure of 6-, 7- stator blade inner ring, 8- spacer member, 9- first order turbine wheel disc rear chamber, The 5th comb tooth sealing structure of 10-, hole on the wheel disc of the second level 11-, the second level 12- turbine wheel disc, the second level 13- turbine wheel disc ante-chamber Room, the 7th comb tooth sealing structure of 14-, 15- turbine cylinder body, the second level 16- turbine wheel disc rear chamber, 17- first through hole, 18- bis- Grade turbine wheel disc lower part cooling chamber, 19- third comb tooth sealing structure, 20- turbine rear axle, 21- axial ring gap, 22- Axle sleeve, the 6th comb tooth sealing structure of 23-, lower chamber between 24- two-stage disk stage, 26- compressor low-pressure stage tap air channel, 27- Air introduction, 28- compressor sub-high pressure grade tap air channel, 29- turbine front end axis, the second through-hole of 30-, 31- level-one turbine wheel Pan bottom cooling chamber, the second comb tooth sealing structure of 32-, 33- gas tight jacket, 34- first order turbine wheel disc front chamber, 35- first Comb tooth sealing structure, 36- blade bottom chamber, 37- fourth hole, 38- level-one turbine wheel disc connection ring, 39- second level turbine wheel Disk connection ring, 40- between centers circulation chamber, 41- shell.

Specific embodiment

Specific embodiment 1: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment The inside cooling structure of rotor, including cooling air guiding device 1, first order turbine wheel disc 5, second level turbine wheel disc 12, thoroughly Flat front end axis 29 and turbine rear axle 20, the turbine front end axis 29 are hollow shaft, and turbine rear axle 20 is arranged before turbine It holds in axis 29, turbine front end axis 29 and the concentric arrangement of turbine rear axle 20, the circumferential direction of the turbine front end axis 29 are provided with Level-one turbine wheel disc connection ring 38, the circumferential direction of the turbine rear axle 20 are provided with second level turbine wheel disc connection ring 39, and first Grade turbine wheel disc 5 is fixedly mounted in level-one turbine wheel disc connection ring 38, and it is saturating that second level turbine wheel disc 12 is fixedly mounted on second level In flat wheel disc connection ring 39；

The cooling air guiding device 1 is used to introduce the cooling air-flow of gas turbine, cooling air guiding device 1 with First order turbine wheel disc 5 forms blade bottom chamber 36 and first order turbine wheel disc front chamber 34, and cooling air-flow flows through the first order Cooling first order root of blade after turbine wheel disc front chamber 34 and blade bottom chamber 36；

Stator blade inner ring 7 is equipped between the first order turbine wheel disc 5 and second level turbine wheel disc 12, in stator blade inner ring 7 Spacer member 8 is installed, it is saturating that spacer member 8 will be separated to form the first order between first order turbine wheel disc 5 and second level turbine wheel disc 12 Flat wheel disc rear chamber 9 and second level turbine wheel disc front chamber 13, cooling air-flow flow through first order turbine wheel disc rear chamber 9 and second Cooling first order root of blade rear side is second with second level root of blade cooling duct is passed through after grade turbine wheel disc front chamber 13 Grade blade provides cooling air；

Lower chamber between two-stage disk stage is formed at the first order turbine wheel disc 5 and 12 lower part of second level turbine wheel disc 24, axis 29 inside in turbine front end forms between centers circulation chamber 40, between centers circulation chamber 40 and two-stage disk stage with turbine rear axle Between lower chamber 24 be connected to；

39 shape of second level turbine wheel disc connection ring that the second level turbine wheel disc 12 and turbine rear axle 20 is circumferentially arranged At second level turbine wheel disc lower part cooling chamber 18, the peace of the second level turbine wheel disc 12 and second level turbine wheel disc connection ring 39 It is radially machined with multiple first through hole 17 at dress, forms the second level between the second level turbine wheel disc 12 and turbine cylinder body 15 Turbine wheel disc rear chamber 16 flows through the cooling air-flow inflow second level turbine wheel disc lower part cooling of lower chamber 24 between two-stage disk stage Chamber 18, and pass through first through hole 17 and enter cooling second level root of blade rear side after second level turbine wheel disc rear chamber 16.Such as This setting, the inside cooling structure of 2 grades of turbine rotors of gas turbine is the combustion gas formed by cylinder body and two stage turbine disk rotors Turbine turbine internal cooling channel, first order turbine wheel disc 5 and its component and second level turbine wheel disc 12 and its component revolving speed Difference, and first order turbine wheel disk rotating speed 5 is greater than 12 revolving speed of second level turbine wheel disc, using chamber, hole, the structural details such as obturages Flow path control and assignment of traffic are carried out to turbine rotor inside, can satisfy cooling system for not coaxial different rotating speeds two-stage Inside turbine offer movable vane piece cooling air, cooling turbine wheel disc, heat-insulated function, used cooling are obturaged to main blast tube Medium is the compressed air from compressor extraction not at the same level.

Specific embodiment 2: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment The inside cooling structure of rotor, the upper end of the cooling air guiding device 1 is using labyrinth gas seals structure 3 and first order turbine The top of wheel disc 5 is coupled, and the middle part of cooling air guiding device 1 and the middle part of first order turbine wheel disc 5 are using the first comb Tooth sealing structure 35 is coupled, and blade bottom is formed on the top of cooling air guiding device 1 and the top of first order turbine wheel disc 5 Portion's chamber 36；The lower part of the cooling air guiding device 1 connects shell, and shell is equipped with gas tight jacket 33, and gas tight jacket 33 is adopted It is coupled with the second comb tooth sealing structure 32 and turbine front end axis 29, cooling air guiding device 1, shell 41, the first order are saturating Flat wheel disc 5 and gas tight jacket 33 form first order turbine wheel disc front chamber 34；Add in the axial direction of the cooling air guiding device 1 Work has multiple third through-holes 2, and 5 top of first order turbine wheel disc is machined with hole 4 on multiple first order wheel discs, third through-hole 2 and first order wheel disc on hole 4 be connected to respectively with blade bottom chamber 36, compressor exhaust cooling air-flow led by cooling air First order turbine rotor vane leaf is passed through by hole 4 on first order wheel disc after entering blade bottom chamber 36 to the third through-hole 2 of device 1 Piece root；The middle position of the first order turbine wheel disc 5 is machined with multiple fourth holes 37, the first order turbine wheel Disk front chamber 34 is connected to by fourth hole 37 with first order turbine wheel disc rear chamber 9.So set, one of compressor exhaust Lease making crosses the third through-hole 2 before first order turbine wheel disc above cooling air guiding device 1 and flows into 5 movable vane of first order turbine wheel disc Blade bottom chamber 36, a part become owner of blast tube, another portion by heel row on front side of the cooling root of blade of labyrinth gas seals structure 3 Divide and first order turbine rotor vane bottom is passed through by hole 4 on first order wheel disc；Compressor hiigh pressure stage bleed is by gas tight jacket 33 and thoroughly The second comb tooth sealing structure 32 that flat front end axis 29 is formed flows into first order turbine wheel disc front chamber 34, cooling first order turbine It is divided into 2 strands of air-flows after on front side of wheel disc, wherein one passes through the between cooling air guiding device 1 and first order turbine wheel disc 5 Blade bottom chamber 36 is met at compressor exhaust airstream after one comb tooth sealing structure 35；Another stock then passes through first order turbine Several fourth holes 37 of axis on wheel disc 5 are passed through the subsequent first order turbine wheel disc rear chamber 9 of first order turbine wheel disc 5, cooling With 8 front side of spacer member on rear side of first order turbine wheel disc, two parts are further divided into, a part of air-flow is saturating by spacer member 8 and the first order Third comb tooth sealing structure 19 between flat wheel disc disk 5 is passed through second level turbine wheel disc front chamber 13, and another part passes through first Grade turbine wheel disc 5 is formed by rear side of the cooling first order turbine blade roots of the 4th comb tooth sealing structure 6 with 7 front of stator blade inner ring Main blast tube is flowed into behind stator blade inner ring front side.

Specific embodiment 3: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment The inside cooling structure of rotor, the lower end for the spacer member 8 installed in the stator blade inner ring 7 is using third comb tooth sealing structure 19 It is coupled with the lower end of first order turbine wheel disc 5.

Specific embodiment 4: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment The 4th comb tooth sealing structure the 6, the 5th comb is respectively adopted in the inside cooling structure of rotor, the left and right ends of the stator blade inner ring 7 Tooth sealing structure 10 is coupled with first order turbine wheel disc 5, second level turbine wheel disc 12.

Specific embodiment 5: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment Pacify inside the between centers circulation chamber 40 that the inside cooling structure of rotor, the turbine rear axle 20 and turbine front end axis 29 are formed Equipped with air introduction 27, between centers circulation chamber 40 is separated to form compressor sub-high pressure grade tap air channel 28 by air introduction 27 With compressor low-pressure stage tap air channel 26, axle sleeve 22, axle sleeve 22 and turbine front end axis are installed in the turbine rear axle 20 By the 6th comb tooth sealing structure 23 between 29, axial ring gap 21 is formed between axle sleeve 22 and second level turbine wheel disc 12, Compressor low-pressure stage tap air channel 26 is connected to by the 6th comb tooth sealing structure 23 with lower chamber 24 between two-stage disk stage, together When, compressor low-pressure stage tap air channel 26 is connected to by axial ring gap 21 with second level turbine wheel disc lower part cooling chamber 18； Level-one turbine wheel pan bottom cooling chamber 31 is formed between the turbine front end axis 29 and first order turbine wheel disc 5, it is described Multiple second through-holes 30 are radially machined on turbine front end axis 29, the compressor sub-high pressure grade tap air channel 28 passes through second Through-hole 30 is connected to level-one turbine wheel pan bottom cooling chamber 31, level-one turbine wheel pan bottom cooling chamber 31 and two-stage disk stage Between lower chamber 24 be connected to.So set, compressor low-pressure stage bleed, is formed by turbine rear axle 20 and air introduction 27 Compressor low-pressure stage tap air channel 26, after the 6th comb tooth sealing structure 23 flow into two-stage disk stage between lower chamber 24； Compressor sub-high pressure grade bleed, by inside center compressor sub-high pressure grade tap air channel 28, using on turbine front end axis 29 Several second through-holes 30 be passed through the level-one turbine wheel pan bottom cooling chamber 31 of first order turbine wheel disc 5, the cooling first order is saturating Behind flat wheel disc lower part, lower chamber 24 between two-stage disk stage is reached；After lower chamber 24 is converged between the above two-stage disk stage, then divide For two strands of air-flows:

Wherein one air-flow along radial inflow to second level turbine wheel disc front chamber 13, and with the portion from hiigh pressure stage Cooling air is divided to converge, the front side of cooling second level turbine wheel disc 12 and the rear side of spacer member 8, then a part passes through the second level Hole 11 is passed through second level turbine rotor vane bottom on second level wheel disc on turbine wheel disc disk, and another part passes through in the stator blade of the second level 7 rear portion of ring and 12 front of second level turbine wheel disc are formed by rear side of the cooling stator blade inner ring of the 5th comb tooth sealing structure 10 and second Main blast tube is flowed into after on front side of grade turbine wheel disc root of blade；

Another stock is saturating along the cooling second level of axial ring gap 21 between second level turbine wheel pan bottom and axle sleeve 22 The second level turbine wheel disc lower part cooling chamber 18 of second level turbine wheel disc and the formation of turbine rear axle 20 is flowed into behind flat wheel pan bottom, Second level turbine wheel disc rear chamber 16 is flowed to outward further along several first through hole 17 in the turbine wheel back-end disk structure of the second level, Main blast tube is discharged to by the 7th comb tooth sealing structure 14 after on rear side of the cooling second level turbine wheel disc of journey, while cooling the On rear side of second level turbine wheel disc root of blade.

Specific embodiment 6: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment The inside cooling structure of rotor, the top of the second level turbine wheel disc 12 are machined with hole 11 on multiple second level wheel discs, the Hole 11 is connected to second level turbine wheel disc front chamber 13 on second level wheel disc, into the cooling air of second level turbine wheel disc front chamber 13 Stream leads to second level turbine rotor vane blade by hole 11 on the wheel disc of the second level.

Specific embodiment 7: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment The inside cooling structure of rotor passes through the 7th comb tooth sealing structure between the second level turbine wheel disc 12 and turbine cylinder body 15 14 are coupled, and the cooling air-flow into second level turbine wheel disc rear chamber 16 flows through cooling the after the 7th comb tooth sealing structure 14 On rear side of second level turbine rotor vane root of blade.

Specific embodiment 8: embodiment is described with reference to Fig. 1, a kind of 2 grades of turbines of gas turbine of present embodiment The inside cooling structure of rotor, the first order turbine wheel disc 5 are connected by screw bolts mode and are fixedly mounted on level-one turbine wheel In disk connection ring 38, the second level turbine wheel disc 12 is fixedly mounted in second level turbine wheel disc connection ring 39.

This embodiment is just an exemplary description of this patent, does not limit its protection scope, those skilled in the art Member can also be changed its part, as long as it does not exceed the essence of this patent, within the protection scope of the present patent.

Claims (10)

1. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine, including cooling air guiding device (1), the first order are saturating Flat wheel disc (5), second level turbine wheel disc (12), turbine front end axis (29), turbine rear axle (20) and shell (41), described is saturating Flat front end axis (29) is hollow shaft, and turbine rear axle (20) setting is in the turbine front end axis (29), turbine front end axis (29) and thoroughly The concentric arrangement of flat rear axle (20), the circumferential direction of the turbine front end axis (29) are provided with level-one turbine wheel disc connection ring (38), the circumferential direction of the turbine rear axle (20) is provided with second level turbine wheel disc connection ring (39), first order turbine wheel disc (5) It is fixedly mounted in level-one turbine wheel disc connection ring (38), second level turbine wheel disc (12) is fixedly mounted on second level turbine wheel disc company It connects on ring (39), it is characterised in that:

The cooling air guiding device (1) is used to introduce the cooling air-flow of the gas turbine from compressor exhaust, cooling Air-deflector (1) and first order turbine wheel disc (5) form blade bottom chamber (36), shell (41) and first order turbine wheel Disk (5) forms first order turbine wheel disc front chamber (34), and cooling air-flow flows through first order turbine wheel disc front chamber (34) and blade Bottom chamber (36) cools down first order root of blade afterwards；

Stator blade inner ring (7) are equipped between the first order turbine wheel disc (5) and second level turbine wheel disc (12), stator blade inner ring (7) it is equipped on spacer member (8), spacer member (8) will separate between first order turbine wheel disc (5) and second level turbine wheel disc (12) It forms first order turbine wheel disc rear chamber (9) and second level turbine wheel disc front chamber (13), cooling air-flow flows through first order turbine Wheel disc rear chamber (9) and second level turbine wheel disc front chamber (13) are cooled down on rear side of first order root of blade afterwards and second level blade root Portion；

Lower chamber between two-stage disk stage is formed at first order turbine wheel disc (5) lower part and second level turbine wheel disc (12) lower part Room (24), turbine front end axis (29) is internal to form between centers circulation chamber (40) with turbine rear axle, between centers circulation chamber (40) with Lower chamber (24) is connected between two-stage disk stage；

The second level turbine wheel disc connection ring (39) that the second level turbine wheel disc (12) and turbine rear axle (20) is circumferentially arranged It is formed second level turbine wheel disc lower part cooling chamber (18), the second level turbine wheel disc (12) and second level turbine wheel disc connection ring (39) installation place is radially machined with multiple first through hole (17), the second level turbine wheel disc (12) and turbine cylinder body (15) Between form second level turbine wheel disc rear chamber (16), the cooling air-flow for flowing through lower chamber (24) between two-stage disk stage flows into two Grade turbine wheel disc lower part cooling chamber (18), and it is cold afterwards into second level turbine wheel disc rear chamber (16) by first through hole (17) But on rear side of the root of blade of the second level.

2. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute The upper end for the cooling air guiding device (1) stated is cooperated using labyrinth gas seals structure (3) and the top of first order turbine wheel disc (5) Installation, the middle part of cooling air guiding device (1) and the middle part of first order turbine wheel disc (5) use the first comb tooth sealing structure (35) it is coupled, blade bottom chamber is formed on the top of cooling air guiding device (1) and the top of first order turbine wheel disc (5) Room (36)；The lower part of the cooling air guiding device (1) is connected with shell (41), and shell is equipped with gas tight jacket on (41) (33), gas tight jacket (33) is coupled using the second comb tooth sealing structure (32) with turbine front end axis (29), cooling air guiding Device (1), shell (41), first order turbine wheel disc (5) and gas tight jacket (33) form first order turbine wheel disc front chamber (34).

3. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute The lower end for the spacer member (8) installed in the stator blade inner ring (7) stated is using third comb tooth sealing structure (19) and first order turbine wheel The lower end of disk (5) is coupled.

4. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute The 4th comb tooth sealing structure (6), the 5th comb tooth sealing structure (10) and the is respectively adopted in the left and right ends for the stator blade inner ring (7) stated Level-one turbine wheel disc (5), second level turbine wheel disc (12) are coupled.

5. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute Air introduction is installed inside the between centers circulation chamber (40) that the turbine rear axle (20) and turbine front end axis (29) stated are formed (27), between centers circulation chamber (40) is separated to form compressor sub-high pressure grade tap air channel (28) and calmed the anger by air introduction (27) Machine low-pressure stage tap air channel (26) is equipped with axle sleeve (22) in the turbine rear axle (20), axle sleeve (22) and turbine front end By the 6th comb tooth sealing structure (23) between axis (29), axial rings are formed between axle sleeve (22) and second level turbine wheel disc (12) Shape gap (21), compressor low-pressure stage tap air channel (26) pass through lower part between the 6th comb tooth sealing structure (23) and two-stage disk stage Chamber (24) connection, meanwhile, compressor low-pressure stage tap air channel (26) passes through axial ring gap (21) and second level turbine wheel disc Lower part cooling chamber (18) connection.

6. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 5, it is characterised in that: institute Level-one turbine wheel pan bottom cooling chamber (31) are formed between the turbine front end axis (29) stated and first order turbine wheel disc (5), institute Multiple second through-holes (30), the compressor sub-high pressure grade tap air channel are radially machined on the turbine front end axis (29) stated (28) it is connected to by the second through-hole (30) with level-one turbine wheel pan bottom cooling chamber (31), level-one turbine wheel pan bottom cooling chamber Room (31) is connected to lower chamber (24) between two-stage disk stage.

7. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute It is machined in the axial direction for the cooling air guiding device (1) stated multiple third through-holes (2), the first order turbine wheel disc (5) Top is machined with hole (4) on multiple first order wheel discs, on third through-hole (2) and the first order wheel disc hole (4) respectively with blade bottom The cooling air-flow of chamber (36) connection, compressor exhaust enters blade by the third through-hole (2) of cooling air guiding device (1) Bottom chamber (36) is passed through first order turbine rotor vane root of blade by hole (4) on first order wheel disc afterwards；

The middle position of the first order turbine wheel disc (5) is machined with multiple fourth holes (37), the first order turbine Wheel disc front chamber (34) is connected to by fourth hole (37) with first order turbine wheel disc rear chamber (9).

8. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute The top for the second level turbine wheel disc (12) stated is machined with hole (11) on multiple second level wheel discs, on the wheel disc of the second level hole (11) with Second level turbine wheel disc front chamber (13) connection, the cooling air-flow into second level turbine wheel disc front chamber (13) pass through the second level Hole (11) are passed through second level turbine rotor vane root of blade on wheel disc.

9. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute It is coupled, is entered by the 7th comb tooth sealing structure (14) between the second level turbine wheel disc (12) stated and turbine cylinder body (15) The cooling air-flow of second level turbine wheel disc rear chamber (16) flows through the 7th comb tooth sealing structure (14), and cooling second level turbine is dynamic afterwards On rear side of leaf root of blade.

10. a kind of inside cooling structure of 2 grades of turbine rotors of gas turbine according to claim 1, it is characterised in that: institute First order turbine wheel disc (5) mode of being connected by screw bolts stated is fixedly mounted in level-one turbine wheel disc connection ring (38), described Second level turbine wheel disc (12) be fixedly mounted in second level turbine wheel disc connection ring (39).