JP3442933B2 - Heat recovery type gas turbine - Google Patents

Description

Detailed Description of the Invention

[0001]

TECHNICAL FIELD The present invention relates to a gas turbine rotor having a steam cooling blade and an air cooling blade.

[0002]

2. Description of the Related Art In order to improve the thermal efficiency of a gas turbine, cooling a gas turbine moving blade with steam has been considered.
In such a type, a new rotor having a passage for supplying steam to the turbine blades and recovering the steam after cooling is required.

In this case, as the cooling steam, bleed air from a steam turbine of a combined cycle is used, but leakage is limited as much as possible on the steam side cycle.

FIG. 2 is a sectional view of a turbine portion of a gas turbine having a steam cooling rotor blade which has been conventionally considered.

As shown in FIG. 2, the cooling steam is supplied to the rotor spindle bolt 3 from the direction of the rotor 31 on the final stage side.
It is supplied through the hole 33 having two gaps and flows into the first-stage rotor blade front chamber 34. After cooling them through the rotor 35 and the rotor blades 36, the second stage rotor 37 of the same shape,
The second stage moving blades 38 are sequentially cooled by passing through the steam, and are recovered from the cooling steam holes 39 of the final stage rotor 31.

[0006]

The supply and recovery of the cooling steam of the steam cooling blade is performed by the above-mentioned route, but considering the effects of efficiency, output, etc., the rear stage (the example shown in the figure). Indicates a third stage rotor blade), and it is possible to cool with a small amount of air.

However, in the case of the type shown in FIG. 2, since the cooling steam supply / recovery passage is complicated, there is no way to provide a cooling air passage on the rotor side even if only some of the moving blades are cooled with air. It was difficult to secure cooling air.

The present invention has been made in view of the above circumstances, and an object thereof is to provide a type having both steam cooling and air cooling.

[0009]

SUMMARY OF THE INVENTION The present invention has been made to solve the above-mentioned problems, and a steam cooling blade and an air cooling blade are provided.
A rotor of a gas turbine with bets, the blades of the front stage and steam cooling the rotor blade, the cooling steam holes in the rotor
It is supplied to the inside of the steam cooling blade to cool the steam.
Configured to be recovered from other holes in the rotor.
The blades in the rear stage are air cooling blades , and the cooling air is
The outer shroud of the stator vane in front of the air-cooled rotor, inside the stator vane,
Through the inner shroud of the stator vane, it is fed into the air cooling blade.
Heat recovery characterized by being configured to be supplied
A gas turbine is provided .

That is, it has a great influence on efficiency, output, etc.
The blades in the front stage should be steam-cooled blades and
The lower stage blades are air cooling blades and are unnecessary
Avoid a complicated structure, and use a simpler structure.
To allow steam, cooling both by air Te, air cooled moving
The supply of cooling air to the rear stage blade was a wing, the air cooling
It arranged vane outer shroud before moving blade, stationary blade Body
Among direct the cooling air through the inner shroud of the stationary blade, so as to supply to the air cooling moving blade of the rear stage, the entire structure
It is possible to make the structure simple and compact .

Further, according to the present invention, the stationary blades for passing the cooling air form a flow path from the stationary blades to the air cooling moving blades via the rotor, and the cooling air connecting portion from the stationary blades to the rotor is Sky
Provide a heat recovery type gas turbine located inside the cooled portion of the air cooling blade and the cooling air outlet hole in the radial direction of the rotor, and supply cooling air from the stationary blade through the rotor to the air cooling blade. At that time, the position where the cooling air is communicated from the vanes to the rotor is located radially inward of the rotor from the cooled portion of the rear air cooling blade and the outlet of the cooling air from the cooled portion. Thus, the cooling air is surely circulated by utilizing the pressure difference between the two positions.

[0012]

BEST MODE FOR CARRYING OUT THE INVENTION An embodiment of the present invention will be described with reference to FIG.

1 is the rotor on the final stage side, 2 is the spindle bolt, 3 is the front chamber of the first stage moving blade, 4 is the rotor on the first stage side, 5
Is the first stage rotor blade, 6 is the second stage rotor blade, 7 is the second stage rotor blade, 8
Is a cooling steam hole, 9 is a cabin, 10 is a so-called air-cooling moving blade of a third stage moving blade, 11 is a stationary blade arranged in front of the moving blade 10 at the last stage, and 12 is an outer side of the stationary blade 11. Shroud, 13
Is also the inner shroud, 14 is the lower part of the inner shroud,
Reference numeral 15 is a seal fin, and 16 is a hole provided in the outer circumference of the third stage rotor 17 in a circumferential direction.

In the present embodiment having such a configuration, the cooling steam is supplied from the direction of the rotor 1 on the final stage side through a hole having a gap in the spindle bolt 2 of the rotor.
It flows into the stage blade front chamber 3.

After passing through the rotor 4 and the rotor blades 5 to cool them, the second stage rotor 6 and the second stage rotor blades 7 of the same type are sequentially cooled by steam, and the cooling steam holes 8 of the final stage rotor 1 are used. Be recovered.

On the other hand, as the cooling air, the extracted air extracted from a gas turbine compressor (not shown) is introduced into the vehicle compartment 9 to cool the air. The seal fin portion 15 passes through the holes in the vane 11, the inner shroud 13, and the lower portion 14 of the inner shroud.
Leading to.

The cooling air discharged to the seal fin portion 15 is supplied from the plurality of holes 16 on the outer periphery of the rotor 17 to the rotor 1.
7 and the rotor blade 10 flow into the seal fin portion 1
The cooling air discharged to 5 is sucked from the rotor hole by the magnitude of the absolute value of the extraction pressure and the pump action action due to the difference ΔH in the height positions of the rotor inlet hole and the rotor outlet hole into the rotor blade 10. It surely flows in and is finally discharged into the main gas stream.

In this embodiment, as described above, the air cooling can be skillfully incorporated without interfering with the steam cooling structure to enable the air cooling.

Although the present invention has been described above with reference to the illustrated embodiments, the present invention is not limited to such embodiments.
It goes without saying that various modifications may be made to the specific structure within the scope of the present invention.

[0020]

Effect of the Invention] According to the heat recovery type gas turbine rotor of the invention of this gun according to claim 1 efficiency in the steam cooling gas turbine employed to improve the output and the like, efficiency, output
The blades in the front stage, which have a large effect on force, are
However, the moving blades in the rear stage, which are less affected, are
And, it avoids unnecessary structure is complicated, and Te than in a more simple structure steam can enable both cooling by air.

[0021] In addition, the intake of cold却空care, the outer shroud of the stationary blade in front of the air cold 却動 <br/> wing, the static in the wings, Doseitsubasa
Since it was specified to be performed via the inner shroud of the above, the simplification and compactness of the entire structure were ensured, and the feasibility was extremely high.

According to the second aspect of the present invention, the cooling air reaching the stationary blade, the rotor, and the target air cooling moving blade is
Due to the pressure difference between the transition position from the stationary blade to the rotor and the transition position to the air-cooling moving blade, the movement of the cooling air becomes reliable and accurate, and the desired cooling function can be achieved.

[Brief description of drawings]

FIG. 1 is a cross-sectional view of a steam-air cooling turbine according to an embodiment of the present invention.

FIG. 2 is a cross-sectional view of a conventionally considered steam cooling turbine.

[Explanation of symbols]

1 Final stage rotor 2 spindle bolt 3 First stage rotor blade front chamber 4 rotor 5 First stage rotor blades 6 Second stage rotor 7 Second stage rotor blade 8 Cooling steam holes 9 car compartment 10 Air cooling blades 11 static wings 12 Outer shroud 13 Inner shroud 14 Lower outer shroud 15 Seal fin 16 holes 17 Third stage rotor

Continuation of the front page (56) Reference JP-A-53-64113 (JP, A) JP-A-50-119115 (JP, A) JP-A-9-13902 (JP, A) JP-A-7-301127 (JP , A) JP-A-3-96628 (JP, A) JP-A-57-176309 (JP, A) (58) Fields investigated (Int.Cl. ⁷ , DB name) F01D 1 / 00-11 / 10 F02C 1/00-9/58 F23R 3/00-7/00

Claims (2)

(57) [Claims] 1. A rotor of a gas turbine having steam cooling blades and air cooling blades, wherein the blades at the front stage are steam cooling blades , and the cooling steam passes through holes in the rotor.
The steam is supplied into the steam cooling blade to cool it
The cooling blade is configured to be recovered from other holes in the rotor , and the rear stage moving blade is an air cooling moving blade , and the cooling air is
Shroud in front of the vane, inside the vane, inside the vane
So that it can be fed into the air cooling blades through the shroud
Heat recovery type gas turbine, characterized by comprising configured. 2. The stationary vane for passing the cooling air is from the stationary vane.
A flow path is formed from the rotor to the air-cooled moving blade,
The cooling air connection from the rotor to the rotor is covered by the air cooling blade.
Inside the cooling section and cooling air outlet hole in the rotor radial direction
Heat recovery type gas turbine according to claim 1, characterized in that was positioned.