JP2001303972A - Re-combustion combined-cycle combination gas turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To enhance the thermal efficiency of a steam turbine driven by the exhaust gas made to increase in temperature and thermal efficiency concurrently with an increase in the temperature and thermal efficiency of combustion gas by heightening the endothermic effect thereof by the cooling by a mixture of dry steam and air. SOLUTION: A re-combustion combined-cycle combination gas turbine is provided with a supply channel 10, a bleed steam gas turbine 23, a fluid cooling mixer 34 and a channel for cooling and supplying fluid, and integrally mounted with a reaction gas turbine 8 having a secondary combustion chamber and composed of a double hollow rotor and plural axial-flow gas turbines 9 whose circumferential side surface is fitted with plural fluid cooling rotor blades in a protruded manner around the side of one end of a rotor shaft 12. The supply channel 10 supplies the combustion gas of a combustor 6, and the turbine 23 is driven by the steam heated by a boiler 20 and a heater 21 mounted halfway through an emission gas passage of a double casing 11. The mixer 34 forms a coolant, which is a highly endothermic mixed fluid of dry steam and air. The channel for cooling and supplying fluid supplies the above coolant to the gas turbines 8, 9.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine in which a rotary shaft is rotated by using a high-temperature and high-pressure combustion gas to extract rotational energy, and more particularly, to a rotary drive board provided around the rotary shaft. The present invention relates to a re-combustion combined cycle mixed gas turbine in which combustion gas is injected in a tangential direction of rotation from an injection nozzle of the above-described type, and a rotation shaft is rotated by utilizing the reaction thereof to extract rotational energy.

[0002]

2. Description of the Related Art Conventionally, a gas turbine has a structure in which high-temperature and high-pressure combustion gas is injected to rotating blades, and the rotating blades are rotated to extract rotational energy. Since high-temperature and high-pressure combustion gas is blown onto the rotating blades, large gas turbines have cooling holes formed in the rotating blades, so that the rotating blades are constantly cooled and prevented from being destroyed by high heat. Have been.

[0003]

However, in the case of a small gas turbine, a cooling hole cannot be formed in the rotating blade, so that the rotating blade is prevented from being destroyed by high-temperature combustion gas. The temperature of the combustion gas is 1000 ° C., which is lower than 1300 ° C. of a large gas turbine, and as a result, there is a problem that a small gas turbine has lower thermal efficiency than a large gas turbine.

The present invention has been made in view of the above problems, and has been made in order to solve the problems. An object of the present invention is to cool a mixture of dry steam and air to absorb heat. By increasing the effect, the temperature of the combustion gas is raised to a temperature similar to that of a large gas turbine, and in particular, the reburning that can simultaneously increase the thermal efficiency of a small gas turbine and the thermal efficiency of a steam turbine driven by the increased exhaust gas It is to provide a combined cycle mixed gas turbine.

[0005]

SUMMARY OF THE INVENTION In order to achieve the above object, an invention according to claim 1 is provided with an intake port at one end of a reburning combined cycle mixed gas turbine body and a double casing at the other end. A combustion gas supply passage for supplying combustion gas from the combustor to the interior of the double cabin, and a rotor shaft connected to the mixed gas turbine body. The rotor shaft is rotatably supported, and one end of the rotor shaft is protruded into the double casing. A recombustion chamber is provided around the one end of the rotor shaft protruding into the double casing. A reaction gas turbine comprising a double hollow rotor having a peripheral side surface and an axial flow gas turbine having a plurality of fluid cooling moving blades projecting at equal intervals on an outer peripheral side surface are integrally provided, and a reaction type gas turbine is provided. Combustion in the afterburning chamber on the circumferential side of the double hollow rotor of the turbine A plurality of combustion gas injection nozzles for injecting gas are provided at equal intervals in the circumferential direction, and each injection nozzle is provided so as to be directed in a circumferential tangential direction around the same direction, and the re-combustion chamber is provided from the rotation center side of the double hollow rotor A secondary fuel supply passage is provided radially toward the combustion gas supply passage, and one side surface of the double hollow rotor is provided in close contact with a combustion gas supply passage whose downstream side is opened inside the double casing, and a combustion gas supply passage is provided. An inlet for communicating with the re-combustion chamber of the double hollow rotor is formed on one side of the double hollow rotor, and a boiler and a superheater are provided in the exhaust gas passage connected to the outlet of the double casing. An extraction steam turbine driven by steam superheated by a boiler and a superheater is provided, and a part of steam and air discharged from the extraction steam turbine are mixed to form a refrigerant of a dry steam-air mixed fluid having a high heat absorption effect. A fluid cooling mixer , Those made of means provided with fluid cooling supply flow passage for supplying the refrigerant generated dry steam air mixture fluid recoil gas turbine and an axial flow gas turbine.

Here, as a preferred embodiment, a fluid cooling vane is provided in the circumferential direction on the inner peripheral surface of the double casing on the outer peripheral side of the combustion gas injection nozzle, and the mixed gas turbine body inside the fluid cooling vane is provided. And a fluid cooling supply channel through which a refrigerant of a dry steam-air mixed fluid that cools the fluid cooling vanes flows. Further, a fluid cooling injection nozzle for injecting a part of the dry steam-air mixed fluid supplied from the fluid cooling supply channel is provided around the combustion gas injection nozzle. Further, the rotor shaft is provided with a low-pressure compressor and a high-pressure compressor which rotate integrally to compress air.

[0007]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, the present invention will be described more specifically based on embodiments of the invention shown in the drawings. Here, FIG. 1 is a cross-sectional view of a reburn combined cycle gas turbine, FIG. 2 is an enlarged cross-sectional view of a main part, FIG. 3 is a front cross-sectional view of a double hollow rotor, and FIG. Front view,
FIG. 5 is a layout diagram of the fluid-cooled vanes provided on the circumferential side of the inner end face inside the double casing.

In FIG. 1, an intake port 1a is formed at one end side of a casing of the reburning combined cycle hybrid gas turbine 1. The intake port 1a is a place where the combustion air is taken in, and the intake port 1a expands, for example, in a trumpet shape, and an output shaft 2a coaxial with the rotor shaft 12 projects outward at the center. An end of the output shaft 2 a protruding outward is linked to the generator 2.

A low-pressure compressor 3 is provided inside the intake port 1a. The low-pressure compressor 3 is a device that compresses air introduced from the intake port 1 a, and the rotation center of the low-pressure compressor 3 is fixed to the other end of the rotor shaft 12. Due to the rotation of the rotor shaft 12, the low-pressure compressor 3 rotates, compresses the combustion air introduced from the intake port 1a at a low pressure and sends it to the downstream side.

The combustion air supply flow path 1b is a flow path for sending the combustion air introduced from the intake port 1a to the downstream combustor 6.
The upstream end is connected to the downstream side of the low-pressure compressor 3, and the downstream end is connected to the combustor 6.

In the middle of the combustion air supply passage 1b, a high pressure compressor 4 for further compressing the combustion air flowing down in the combustion air supply passage 1b is provided. The high-pressure compressor 4 is fixed to a rotor shaft 12 coaxial with the low-pressure compressor 3. The rotation of the rotor shaft 12 causes the high-pressure compressor 4 to rotate, and the combustion air flowing down the combustion air supply passage 1 b. Is further compressed to a high pressure and sent to the combustor 6 under pressure.

An intermediate cooler 5 is formed in the combustion air supply passage 1b downstream of the low pressure compressor 3 and is compressed by the water flowing through the intermediate cooler 5 and heated by the low pressure compressor 3. The compressed air for combustion is cooled. The compression ratio in the combustor 6 can be increased by intercooling the compressed air.

The combustor 6 is a chamber for generating combustion gas. The combustor 6 is connected to a fuel injection valve 6a for supplying fuel, and to the downstream end of the combustion air supply passage 1b as described above. I have. An unillustrated spark plug for burning a mixture of combustion air and fuel is provided in the combustor 6.

A combustion gas supply passage 10 is formed downstream of the combustor 6. The downstream side of the combustion gas supply passage 10 is connected to the inner end surface 11b of the double casing 11 by opening it in a ring shape.

The interior of the double casing 11 has, for example, a truncated cone shape, and gradually increases in diameter toward the discharge port 11a. The maximum diameter side is the discharge port 11a. The diameter of the double casing 11 opposite to the discharge port 11a and having the smallest diameter is a circular rear end face 11b. The double casing 11 is provided on the other end side of the casing of the reburning combined cycle hybrid gas turbine 1, and is located on the opposite side of the intake port 1a.

A circular rear end surface 11b inside the double casing 11
One end of the rotor shaft 12 protrudes from the center of the shaft. The rotor shaft 12 penetrates through the center of the rear end face 11b inside the double casing 11, and the reburning combined cycle mixed gas turbine 1
The other end side protrudes toward the above-described intake port 1a side. Further, the low-pressure compressor 3 and the high-pressure compressor 4 described above are fixed on the way.

The outer periphery of a portion of the rotor shaft 12 protruding from the rear end face 11b inside the double casing 11 is provided with a heat-resistant alloy material 12
a is coated. The mixed gas turbine 7 is integrally provided on the rotor shaft 12 coated with the heat-resistant alloy material 12a. The rotor shaft 12 is integrally attached to a rotation center of the mixed gas turbine 7.

The mixed gas turbine 7 attached to the center of rotation of the rotor shaft 12 comprises a reaction gas turbine 8 on the rear end face 11b side and an axial gas turbine 9 on the discharge port 11a side. The reaction gas turbine 8 and the axial gas turbine 9 are integrally formed in the front-rear direction.

The reaction type gas turbine 8 is formed of a double hollow rotor 13 mounted on the outer periphery of a rotor shaft 12, and the double hollow rotor 13 has a circumferential side surface 13a on its outer circumferential side.
And the inside has a hollow cylindrical shape. A recombustion chamber 14 is formed in the hollow interior of the double hollow rotor 13.

The reburning chamber 14 is formed in a ring shape on the circumferential side of the double hollow rotor 13. The reburning chamber 14 is a place where the combustion is performed based on the supplied combustion gas, a dry steam-air mixed fluid described later, a secondary fuel, and the like to generate a high-temperature and high-pressure secondary combustion gas. It is injected from the combustion gas injection nozzle 15.

On the circumferential side surface 13a of the double hollow rotor 13, a plurality of combustion gas injection nozzles 15 for injecting the combustion gas burned in the reburning chamber 14 are provided. The plurality of combustion gas injection nozzles 15 are provided at equal intervals in the circumferential direction of the circumferential side surface 13a. Each combustion gas injection nozzle 15 is provided so as to be directed in a circumferential tangential direction in the same rotational direction. The back side of each combustion gas injection nozzle 15 communicates with the reburning chamber 14.

The double hollow rotor 13 inside the reburn chamber 14
A secondary fuel supply flow path 16 is formed radially from the rotor shaft 12 to the ring-shaped re-combustion chamber 14 in the hollow interior. A secondary fuel injection valve 16a is formed at the downstream end of the distal end of the radial secondary fuel supply passage 16 so that the secondary fuel is supplied from the secondary fuel injection valve 16a at the downstream end to the reburning chamber 14. Has become.

The secondary fuel supply passage 16 is connected to the rotation center of the rotor shaft 12 on the upstream side, and to the rotation center of the rotor shaft 12 in the axial direction of the other end. The next fuel supply passage 16b is formed, and its upstream side is bent in the direction perpendicular to the axis on the way, and has an opening 16c in the peripheral surface located on the rotor shaft 12 inside the casing.

In the casing around the opening 16c of the rotor shaft 12, a supply connection groove 16d is formed in the circumferential direction thereof. A ring-shaped oil seal 16g is attached to both sides of the supply connection groove 16d to prevent fuel leakage. Further, a sealed slide bearing 16h for bearing the rotor shaft 12 is provided adjacent to the oil seal 16g.

A secondary fuel supply passage 16e is formed in the casing, a secondary fuel control valve 16i is provided in the middle thereof, and a downstream end thereof is connected to a supply connection groove 16d.
The upstream end of the secondary fuel supply passage 16e is open to the outer peripheral surface of the casing, and one end of the secondary fuel nozzle 16f is connected to the opening.

The rotor shaft 1 on the inner side of the double hollow rotor 13
A fluid cooling supply channel 17 is formed in a ring shape around 2. Further, double radially oriented blades 17a are formed radially from the ring-shaped fluid cooling supply channel 17 toward the outer combustion side combustion chamber 14. Some double radial blades 17
a is formed outside the radially formed secondary fuel supply passage 16. Radial double radial blade 17
a is connected to the reburning chamber 14 by a boss formed at the boundary with the reburning chamber 14 and the fluid cooling supply hole 17b.
A reinforcing member 17c for reinforcing the double radial blade 17a is provided.

Further, on both sides of the reburning chamber 14, circumferential side surfaces 1 are provided.
A fluid cooling injection nozzle 18a is formed toward the combustion gas injection nozzle 15 of 3a. The fluid cooling jet nozzle 18a is in communication with the double radial blade 17a, and a part of the air in the double radial blade 17a enters the fluid cooling nozzle 18a.

A fluid cooling injection nozzle 18 is formed on the outer periphery of each combustion gas injection nozzle 15 in the same injection direction as the nozzle 15. The fluid cooling jet nozzle 18a is connected to the fluid cooling jet nozzle 18a. The air that has flowed down from the fluid cooling injection nozzle 18a is injected from the fluid cooling injection nozzle 18 and is used as a driving force to rotate the double hollow rotor 13 by its reaction and rotate the double hollow rotor 13.

The combustion gas and the air from the fluid cooling injection nozzle 18 are injected from the combustion gas injection nozzles 15 provided on the circumferential side surface 13a of the double hollow rotor 13 at equal intervals. The rotor 13 is driven to rotate coaxially about the rotor shaft 12 to extract rotational energy. Rotational energy is extracted from an output shaft 2a interlocked with the other end of the rotor shaft 12.

The axial-flow gas turbine 9 integrally formed behind the reaction gas turbine 8 has a plurality of fluid-cooling moving blades 19a radially protruding from a circumferential side surface as an outer periphery thereof. The exhaust gas injected from the reaction gas turbine 8 hits and rotates these fluid-cooled moving blades 19a, so that the exhaust gas is further driven to rotate coaxially around the rotor shaft 12 and the rotational energy is reduced. It takes out more than the single case.

Each fluid-cooled moving blade 19a protruding from the outer periphery of the axial-flow gas turbine 9 has its base end connected to each shank 19c mounted inside the axial-flow gas turbine 9 via each platform 19b. ing. The base end of each shank 19c is connected to the outer periphery of the rotor shaft 12 via each implant 19d.

A fluid cooling supply hole 19 is provided at the boundary between the interior of the axial gas turbine 9 and the interior of the reaction gas turbine 8.
e, a part of the refrigerant of the dry steam-air mixed fluid described below that cools the reaction gas turbine 8 flows into the axial flow type gas turbine 9 through the fluid cooling supply hole 19e, and the axial flow type The gas turbine 9 is cooled.

Each of the shank 19c and the implant 19d is mounted on a hollow rotor 19f inside the gas turbine 9 of the axial flow type. The portion to which this implantation part 19d is connected is a boss and a fluid cooling supply hole 17b, and the refrigerant of the dry steam-air mixed fluid flowing in from the fluid cooling supply hole 19e passes through the fluid cooling supply hole 17b to the hollow rotor 19f. The shank 19c and the implant 19d are cooled by the refrigerant of the dry steam-air mixed fluid that has flowed into the hollow rotor 19f, and the fluid cooling blade 19a is also cooled via the platform 19b. .

The casing of the inner end surface 11b inside the double casing 11 has a fluid cooling supply passage 1
7d is formed, and the fluid cooling supply channel 17d communicates with the fluid cooling supply channel 17 formed in a ring shape around the rotor shaft 12.

The fluid cooling supply channel 17d is provided with a fluid cooling supply channel 17e which forms the upstream side thereof. The fluid cooling supply passage 17e is formed inside the casing, and the upstream side forms the peripheral surface side of the double casing 11, and the double casing outlet 36 of the double casing 11 and The upstream end of the fluid cooling supply channel 17 e is connected to the fluid cooling mixer 34 via the double casing inlet 35.

An inlet 13b is formed on the side surface of the double hollow rotor 13 at a location in contact with the downstream side of the combustion gas supply flow path 10 which is formed in a ring shape on the inner end surface 11b inside the double casing 11 and has a ring shape. I have. The inlet 13b is formed in a plurality of fan-like shapes divided between the radially formed secondary fuel supply passage 16 and the double radial blade 17a, and the combustion gas flowing down the combustion gas supply passage 10 is formed. Enters the reburning chamber 14 of the double hollow rotor 13 through the inlet 13b.

The axial-flow gas turbine 9 on the opposite side of the portion where the inlet 13b is formed has a heat-resistant cap 13c in the shape of a truncated cone whose diameter decreases toward the outlet 11a inside the double casing 11. Installed. Heat-resistant cap 13c
Are the combustion gas injection nozzle 15 and the fluid cooling injection nozzle 18
To the exhaust port 11a.

Further, a rear end face 11b inside the double cabin 11
A labyrinth seal 13d for preventing the combustion gas flowing down from the combustion gas supply flow path 10 from leaking is attached in a ring shape between the double hollow rotor 13 and the side surface of the double hollow rotor 13 in contact with the labyrinth seal.

A fluid cooling vane 19 is formed in the circumferential direction on the circumferential side of the inner end surface 11b inside the double casing 11. For example, a channel diffuser is used for the fluid cooling vane 19. A part of the fluid cooling supply passage 17 e for cooling the fluid cooling vane 19 is formed in a ring shape in a casing inside the fluid cooling vane 19, and the fluid cooling static passage of the double casing 11 is formed. The wing 19 is prevented from being destroyed by high heat.

The fluid-cooled vanes 19 supply the combustion gas injected from the combustion gas injection nozzles 15 provided at equal intervals on the circumferential side surface 13a of the double hollow rotor 13 and the air injected from the fluid-cooled injection nozzle 18. It reflects and enhances its recoil, and fulfills the function of increasing the rotational force of the double hollow rotor 13 due to the recoil.

An exhaust gas passage 11c through which exhaust gas injected from the reaction gas turbine 8 is discharged is integrally connected to an exhaust port 11a inside the double casing 11. A boiler 20 and a superheater 21 that are superheated by the exhaust gas are provided in the middle of the exhaust gas passage 11c. The upstream side of the superheater 21 is connected to the boiler 20.

The downstream side of the superheater 21 is connected to a bleed-type steam turbine 23.
2 are provided. An output shaft 2a is connected to the extraction steam turbine 23, and an end of the output shaft 2a is connected to the generator 2. The driving force of the extraction steam turbine 23 generates electric power via the output shaft 2a. The power is generated by driving the machine 2.

The condenser 24 is a device for returning the steam that drives the bleeding steam turbine 23 to water. The condensate pump 25 is a pump that supplies a refrigerant, for example, cooling water, used for returning steam to water to the condenser 24. Water supply pump 27
Supplies distilled water returned from steam in the condenser 24 to the boiler 20.
Pump.

A part of the refrigerant supplied to the condenser 24 by the condensate pump 25 and used for the condensate is used as the refrigerant of the intercooler 5 while being controlled by the condensate control valve 26 for the intercooler. You.

The fresh water generator 28 is a device for producing distilled water supplied to the boiler 20, and the distilled water produced by the fresh water generator 28 is stored in a distilled water tank 29. The distilled water control valve 30 is a device for controlling the amount of distilled water supplied from the distilled water tank 29,
A shortage of distilled water supplied from the condenser 24 to the boiler 20 is controlled by the distilled water control valve 30 and added thereto, and then supplied to the boiler 20 by the water supply pump 27.

Incidentally, the bleeding steam turbine 23
Of the low-temperature steam and the medium-temperature steam are the low-temperature steam control valve 32 and the medium-temperature steam control valve 3 respectively.
It is sent to the fluid cooling mixer 34 while being controlled by 3. The air cooled by the intercooler 5 is sent to the fluid cooling mixer 34 while being controlled by the cooling air control valve 31.

The fluid-cooled mixer 34 mixes the sent dry steam and air to generate a refrigerant of a dry steam-air mixed fluid. The refrigerant of the dry steam-air mixed fluid generated by mixing in the fluid cooling mixer 34 has a larger heat capacity than a refrigerant of air alone, and therefore has a large heat absorbing effect.

The refrigerant of the dry steam-air mixed fluid having a large heat absorbing effect generated by the fluid cooling mixer 34 is
Flows down through the double casing inlet 35 and the double casing outlet 36 to the reaction gas turbine 8 and the axial flow gas turbine 9 through the fluid cooling supply passages 17e and 17d. 8 and the axial gas turbine 9 are cooled. Reaction gas turbine 8 and axial gas turbine 9
Is cooled by the refrigerant of the dry steam-air mixed fluid having a large endothermic effect, so that it is cooled more than air cooling.

Next, the operation based on the configuration of the embodiment of the present invention will be described below. The rotor shaft 12 is rotated by a starting motor (not shown). By the rotation of the rotor shaft 12, the low-pressure compressor 3 rotates to suck air from the intake port 1a. The sucked air is compressed by the low-pressure compressor 3 and sent to the combustion air supply channel 1b under pressure.

The air compressed by the low-pressure compressor 3 is
The cooling air control valve 31 is cooled by the intercooler 5 while flowing down the combustion air supply passage 1b.
The compressed air is sent to the fluid-cooled mixer 34 while being compressed by the high-pressure compressor 4 on the way, and supplied to the combustor 6.

Compressed air is supplied to the combustor 6 through a combustion air supply passage 1b, and fuel is supplied from a fuel injection valve 6a. A mixture of these is burned by a spark plug (not shown), A high-temperature and high-pressure combustion gas is generated therein. The combustion gas enters the inside of the double casing 11 through the combustion gas supply passage 10.

The combustion gas entering the interior of the double cabin 11 is
From the inlet 13b of the double hollow rotor 13, it enters the reburning chamber 14 inside the double hollow rotor 13. This reburning chamber 14
Is supplied with the secondary fuel through the secondary fuel supply passage 16,
Further, the boss of the double radial blade 17a and the fluid cooling supply hole 17 are provided.
After b, the reaction gas turbine 8 and the axial gas turbine 9 are cooled and a part of the superheated dry steam-air mixed fluid is supplied.

In the re-combustion chamber 14 of the double hollow rotor 13, the combustion gas, the secondary fuel, and the dry steam-air mixed fluid are burned to generate high-temperature and high-pressure combustion gas. The high temperature and high pressure combustion gas is supplied to the circumferential side surface 13a of the double hollow rotor 13.
Are injected from the combustion gas injection nozzles 15 provided at equal intervals.

Since the injection direction of the combustion gas injection nozzles 15 is the same rotation direction, the double hollow rotor 13 rotates in a fixed direction due to the reaction of the combustion gas injected from each combustion gas injection nozzle 15. At this time, since the dry steam-air mixed fluid is simultaneously injected from the fluid cooling injection nozzles 18 around each combustion gas injection nozzle 15, the rotational driving force of the double hollow rotor 13 due to the reaction is increased.

Further, a fluid cooling vane 19 is provided on a circumferential side of a rear end face 11b inside the double casing 11, which is an injection side of each combustion gas injection nozzle 15 and a fluid cooling injection nozzle 18. The combustion gas and the dry steam-air mixed fluid injected from each of the combustion gas injection nozzles 15 and the fluid cooling injection nozzle 18 are reflected by the fluid cooling vanes 19, and the recoil is further increased. The rotational driving force is further increased.

The combustion gas injected from each of the combustion gas injection nozzles 15 and the fluid cooling injection nozzles 18 and the dry steam-air mixed fluid that has cooled the reaction gas turbine 8 and the axial flow gas turbine 9 and has been superheated are: Fluid-cooled moving blade 1 of axial-flow gas turbine 9 located behind reaction gas turbine 8
9a, which is rotated to further increase the rotational driving force of the rotor shaft 12.

Then, the high-temperature and high-pressure combustion gas having the rotor shaft 12 rotated and the cooled and superheated dry steam-air mixed fluid are discharged from the discharge port 11a inside the double casing 11 to the discharge gas passage 11c. You.

The high-temperature and high-pressure combustion gas discharged into the exhaust gas passage 11c and the cooled and superheated dry steam-air mixed fluid flow through the exhaust gas passage 11c, and the boiler provided in the exhaust gas passage 11c. 20 and the superheater 21 are overheated. The superheater 21 is superheated by absorbing heat from the high-temperature and high-pressure combustion gas and the cooled and superheated dry steam-air mixed fluid.

The steam flowing through the superheater 21 is superheated and enters the extraction steam turbine 23 to drive the extraction steam turbine 23. In this case, the combustion gas in the exhaust gas that overheats the steam has a high temperature and a high pressure for the above-described reason. Therefore, the steam is superheated to drive the bleeding steam turbine 23, and the thermal efficiency is increased.

A part of the steam driven by the extraction steam turbine 23 is sent to the condenser 24 to be returned to water, and returned to the boiler 20 by the water supply pump 27 again. The remaining steam is sent to the fluid cooling mixer 34 while being controlled by the low temperature steam control valve 32 and the medium temperature steam control valve 33.

From the extraction steam turbine 23, a low-temperature steam control valve 32 and a medium-temperature steam control valve 33 pass through a fluid cooling mixer 34.
Is mixed with the compressed air supplied from the combustion air supply passage 1b while being controlled by the cooling air control valve 31, and becomes a dry steam-air mixed fluid refrigerant. Since the dry steam-air mixed fluid has a larger heat capacity than the air alone, when the dry steam-air mixed fluid is used as a refrigerant, the heat absorbing effect is large.

The refrigerant of the dry steam-air mixed fluid generated by the fluid cooling mixer 34 is provided on the inner side of the double casing 11 while flowing from the double casing entrance 35 to the double casing exit 36. The cooled fluid-cooled vane 19 is cooled to prevent the fluid-cooled vane 19 from being thermally damaged by the high-temperature and high-pressure combustion gas.

The refrigerant of the dry steam-air mixed fluid flowing down the double casing outlet 36 flows down the fluid cooling supply passages 17e and 17d and from the fluid cooling supply passage 17 to the double hollow rotor of the reaction gas turbine 8 13 to cool the inside. A part of the refrigerant of the dry steam-air mixed fluid flowing into the double hollow rotor 13 flows from the fluid cooling supply hole 19e into the hollow rotor 19f of the adjacent axial flow gas turbine 9 to cool the inside thereof. I do.

Double hollow rotor 1 of reaction gas turbine 8
A part of the dry steam-air mixed fluid that has been cooled by cooling the hollow rotor 19f of the gas turbine 9 and the axial flow type gas turbine 9 is partially sent to the re-combustion chamber 14 and used as combustion air, and the rest is fluid cooled. The gas is injected from the injection nozzle 18 and is used as a driving force for rotating the reaction gas turbine 8 by the reaction of the injection.

In this case, the reaction gas turbine 8
The axial-flow gas turbine 9 is cooled by the refrigerant of the dry steam-air mixed fluid having a high endothermic effect generated by the fluid cooling mixer 34, and thus is sufficiently cooled.

For this reason, even when the temperature of the combustion gas is increased, the reaction type gas turbine 8 is sufficiently cooled by the refrigerant of the dry steam-air mixed fluid having a high heat absorbing effect, so that thermal damage is avoided, and high temperature and high pressure Combustion gas can be injected, and a decrease in thermal efficiency can be prevented.

The axial flow type gas turbine 9 is also sufficiently cooled by the dry steam-air mixed fluid having a high heat absorbing effect even when the combustion gas of high temperature and high pressure is applied, so that thermal damage is avoided.

It should be noted that the present invention is not limited to the above embodiment of the present invention, and it is needless to say that various modifications can be made without departing from the spirit of the present invention.

[0069]

As is apparent from the above description, according to the reburning combined cycle mixed gas turbine according to the present invention, the gas turbine is cooled by a mixed fluid of dry steam and air having a high endothermic effect. The turbine can be cooled sufficiently, so that even if the gas turbine is driven with higher heat, the occurrence of thermal damage can be avoided, so that high-temperature and high-pressure combustion gas can be injected, thereby preventing a decrease in thermal efficiency. Can be. In addition, since high-temperature and high-pressure combustion gas is injected, the temperature of the exhaust gas also increases, and the boiler that is overheated by the exhaust gas can be overheated at a high temperature, and the efficiency of the steam turbine driven by the steam heated by the boiler can be simultaneously increased Etc., which are extremely novel and beneficial.

[Brief description of the drawings]

FIG. 1 is a cross-sectional view of a reburning combined cycle hybrid gas turbine showing an embodiment of the present invention.

FIG. 2 is an enlarged sectional view of a main part showing the embodiment of the present invention.

FIG. 3 is a front sectional view of the double hollow rotor showing the embodiment of the present invention.

FIG. 4 is a front view of a double hollow rotor showing an embodiment of the present invention.

FIG. 5 is a layout view of a fluid-cooled vane provided on a circumferential side of a rear end face inside a double casing, showing an embodiment of the present invention.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Reburning combined cycle hybrid gas turbine 1a Inlet 1b Combustion air supply channel 2 Generator 2a Output shaft 3 Low pressure compressor 4 High pressure compressor 5 Intercooler 6 Combustor 6a Fuel injection valve 7 Mixed gas turbine 8 Reaction Type gas turbine 9 Axial flow type gas turbine 10 Combustion gas supply flow path 11 Double casing 11a Exhaust port 11b Back end face 11c Exhaust gas path 12 Rotor shaft 13 Double hollow rotor 13a Circular side face 13b Inlet 13c Heat-resistant cap 13d Labyrinth Seal 14 Reburning chamber 15 Combustion gas injection nozzle 16 Secondary fuel supply passage 16a Secondary fuel injection valve 16b Secondary fuel supply passage 16c Opening 16d Supply connection groove 16e Secondary fuel supply passage 16f Secondary fuel nozzle 16g Oil Seal 16h Sealed thrust bearing 16i Secondary fuel control valve 17 Fluid cooling supply channel 1 a Double Radial Direction Blade 17b Boss and Fluid Cooling Supply Hole 17c Reinforcement 17d Fluid Cooling Supply Channel 17e Fluid Cooling Supply Channel 18 Fluid Cooling Injection Nozzle 18a Fluid Cooling Injection Nozzle 19 Fluid Cooling Stator Blade 19a Fluid Cooling Blade 19b Platform Reference Signs List 19c Shank 19d Implantation part 19e Fluid cooling supply hole 19f Hollow rotor 20 Boiler 21 Superheater 22 Superheated steam control valve 23 Extraction steam turbine 24 Condenser 25 Condensate pump 26 Condensate control valve for intermediate cooler 27 Feed pump 28 Water tank 29 Distilled water tank 30 Distilled water control valve 31 Cooling air control valve 32 Low temperature steam control valve 33 Medium temperature steam control valve 34 Fluid cooling mixer 35 Double cabin inlet 36 Double cabin outlet

──────────────────────────────────────────────────続 き Continued on the front page (51) Int.Cl. ⁷ Identification symbol FI Theme coat ゛ (Reference) F01K 23/10 F01K 23/10 T

Claims (4)

[Claims] An air inlet is provided at one end of a combined re-combustion cycle gas turbine main body, a double casing is provided at the other end, and a combustor for burning air and fuel sucked from the air inlet is provided. A combustion gas supply passage for supplying combustion gas from the heat exchanger to the interior of the double casing, rotatably supporting the rotor shaft on the mixed gas turbine body, and connecting one end of the rotor shaft to the interior of the double casing. A reaction type gas turbine comprising a double hollow rotor having a recombustion chamber therein and having a circumferential side around one end of a rotor shaft protruding into the double casing and a circumferential side of the outer circumference An axial flow gas turbine with a plurality of fluid cooling blades protruding at equal intervals is provided integrally, and the combustion gas burned in the reburning chamber on the circumferential side surface of the double hollow rotor of the reaction gas turbine. Multiple combustion gas injection nozzles to be injected are provided at equal intervals in the circumferential direction And each injection nozzle is provided so as to be directed in a circumferential tangential direction around the same direction, and a secondary fuel supply flow path is radially provided from the rotation center side of the double hollow rotor toward the reburning chamber. One side surface is provided in close contact with the combustion gas supply passage whose downstream side is opened inside the double casing, and the inlet for conducting the combustion gas supply passage and the re-combustion chamber of the double hollow rotor is doubled. A bleed-type steam turbine formed on one side of the hollow rotor and provided with a boiler and a superheater in the middle of an exhaust gas passage connected to the discharge port of the double casing, and driven by the steam heated by the boiler and the superheater. A fluid cooling mixer that mixes some of the steam and air discharged from the extraction steam turbine to generate a refrigerant of a dry steam-air mixed fluid having a high endothermic effect, and a refrigerant of the generated dry steam-air mixed fluid is provided. The reaction gas turbine and Reburn combined cycle 混式 gas turbine, characterized in that a axial flow gas turbine to supply fluid cooling supply flow passage. 2. A fluid-cooling vane is provided in a circumferential direction on an inner peripheral surface of a double casing on an outer peripheral side of a combustion gas injection nozzle, and a fluid-cooling vane is provided on a mixed gas turbine body inside the fluid-cooling vane. 2. A reburning combined cycle mixed gas turbine according to claim 1, further comprising a fluid cooling supply passage through which a refrigerant of a dry steam-air mixed fluid that cools the cooling water flows. 3. The re-burning combined cycle mixing device according to claim 1, further comprising a fluid cooling injection nozzle for injecting a part of the dry steam-air mixed fluid supplied from the fluid cooling supply passage around the combustion gas injection nozzle. Gas turbine. 4. The reburning combined cycle hybrid gas turbine according to claim 1, wherein the rotor shaft is provided with a low-pressure compressor and a high-pressure compressor that rotate integrally to compress air.