JP2000179302A - Gas turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To improve capability of a turbine stage by forming in a turbine nozzle, and specifically, at a specific blade height of the turbine nozzle, an outlet port for discharging a cooling medium to the outside, in the case where a turbine rotor blade has a specific aspect ratio. SOLUTION: A turbine stage 14 is formed by an upstream turbine nozzle 12 and a downstream turbine rotor blade 13. An axial-flow gas turbine is formed by disposing a plurality of turbine stages 14. When the turbine rotor blade 13 having an aspect ratio (ratio of blade height to chord length) of 1.5 or less is embodied in such a gas turbine, a plurality of outlet ports are formed in the trailing edge of the turbine nozzle 12 at positions within the ranges of 0 to 25% and 75 to 100% of the overall blade height of the turbine nozzle 12. Thus, high-pressure air C after cooling the blade is discharged from the outlet ports. As a result, a flow rate to the top and bottom portions of the turbine rotor blade 13 is increased, whereby capability of the turbine stages is improved.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine for improving the performance of a turbine stage in which a turbine nozzle and a turbine blade are combined.

[0002]

2. Description of the Related Art In recent gas turbines, the gas turbine driving gas (hereinafter referred to as the main stream) at the entrance thereof is further raised in temperature for economical operation, and the gas turbine output per unit is increased. Tend to increase.

[0003] In order to further increase the temperature of the mainstream,
Turbine nozzles and turbine blades that constitute the turbine stage generate excessive thermal strain and thermal stress due to local heating,
It has become difficult to maintain the strength of the wing material high.
For this reason, the gas turbine supplies high-pressure air extracted from the air compressor to the turbine nozzles 1a and 1b arranged in an annular row in the circumferential direction of the turbine shaft for cooling as shown in FIG. We deal with high temperature.

[0004] On the other hand, the high-pressure air after cooling the inside of the blade is supplied to outlet holes 3 provided in the trailing edges 2a, 2b of the turbine nozzles 1a, 1b.
a, 3b and outflow holes 6a, 6b provided in the back sides 5a, 5b of the front edges 4a, 4b, and the turbine nozzles 1a,
It joins with the main stream 8 which expands in the flow path 7 formed between 1b.

[0005] The main stream 8 after the merging is supplied to a turbine blade (not shown), where the direction of the flow is changed, and the main stream 8 is sequentially supplied to a turbine nozzle and a turbine blade of the next stage. As shown in FIG. 15, the high-pressure air after cooling the blades that merges with the main stream 8 has a flow rate ratio (ratio of the high-pressure air to the main stream).
Is 2.0%, the turbine nozzle loss is maximized, and when the flow rate ratio exceeds 4.0%, the turbine nozzle performance is improved. However, when the flow rate ratio is increased, the temperature of the main stream 8 decreases, Since the output of the gas turbine is reduced, the flow rate ratio is empirically set in consideration of maintaining the strength of the blade material and reducing the output of the gas turbine.

[0006]

Another factor in reducing gas turbine output is secondary flow losses.

Conventionally, as shown in FIG. 13, a gas turbine has annular outer ring walls 9 and inner ring walls 10 on the top and bottom sides of turbine nozzles 1a and 1b, respectively, and is formed between turbine nozzles 1a and 1b. Since the flow path 7 to be formed is limited, a boundary layer develops around the outer ring wall 9 and the inner ring wall 10, and the flow of the main flow 8 on the outer ring wall 9 side and the inner ring wall 10 side is reduced.

Further, of the turbine nozzles 1a and 1b,
Between the ventral side F of one turbine nozzle 1b and the dorsal side B of the adjacent turbine nozzle 1a, there is a pressure gradient in which the pressure on the ventral side F is high and the pressure on the dorsal side B is low. When the main flow 8 turns in the flow path 7 in such a state, the turbine nozzle 1
At the center of the blade heights a and 1b, the generated centrifugal force and the pressure gradient are balanced, and the flow of the main flow 8 is made favorable.

However, on the outer ring wall 9 side and the inner ring wall 10 side of the turbine nozzles 1a and 1b, the flow velocity of the main flow 8 is slow and the centrifugal force is small, so that the balance with the pressure gradient is lost. Flow, so-called secondary flow. At this time, a channel vortex 11 is generated. Channel vortex 1
1 involves the mainstream 8 and eventually grows large, and the mainstream 8
Disrupt the flow of This causes a loss due to the secondary flow.

[0010] The loss due to the secondary flow also occurs in the turbine rotor blades, which causes the blade performance to deteriorate. For example, in a turbine rotor blade having an aspect ratio (ratio of blade height to chord length) of 1.5 or less, flow path vortices 7 generated on the rotor disk side and the heat shield segment side interfere with each other near the center of the blade height. Then, as shown in FIG. 3, the turbine rotor blade total pressure loss coefficient at the outlet increases at the position of the center of the blade height. Since the turbine blade total pressure loss coefficient is a loss per turbine blade, it is 1 when integrated.
The cascade loss of the turbine rotor blades per paragraph is calculated. Here, the turbine blade total pressure loss is defined as the ratio of the dynamic pressure at the outlet to the difference between the total pressure at the inlet and the total pressure at the outlet.

Further, for example, in the case of a turbine blade having an aspect ratio of 1.2 or more, as shown in FIG. 9, the turbine blade total pressure loss coefficient on the rotor disk side and the heat insulation segment side is high, and the center portion of the blade height is high. It is smaller in position.

By the way, in the conventional gas turbine, when the high-pressure air having cooled the turbine nozzles 1a and 1b is joined to the main stream 8, the high-pressure air is blown out almost uniformly from each position of the blade height of the turbine nozzles 1a and 1b. Was.

However, high-pressure air is supplied to the turbine nozzles 1a,
Even when air is blown out almost evenly from each position of the blade height of 1b, the turbine blade has a large turbine blade total pressure loss coefficient. This turbine rotor blade total pressure loss coefficient is due to the flow path vortex 11. Considering that it is difficult to eliminate the loss due to the secondary flow with the current technology, the high pressure air blown from the turbine nozzles 1a and 1b is considered. In the gas turbine, it is better to reduce the outflow to the area where the turbine blade total pressure loss coefficient is high, and to increase the outflow to the area where the turbine blade total pressure loss coefficient is low, and to reduce the loss as a whole. Output is expected to increase.

At this time, the turbine blade has a small geometric outflow angle so that high-pressure air flows more toward the region where the turbine blade total pressure loss coefficient is low, and has a region where the turbine blade total pressure loss coefficient is high. It may be necessary to increase the geometric outflow angle so that the high pressure air flowing to the side is reduced.

The present invention has been made based on such an idea. When the high-pressure air after cooling the blades from the turbine nozzle to the turbine blades flows out, the region where the turbine blade total pressure loss coefficient is lower is more. It is an object of the present invention to provide a gas turbine in which the gas flows out to increase the gas turbine output.

Another object of the present invention is to provide a high-pressure air after cooling blades from a turbine nozzle to a turbine blade, so that the high-pressure air can flow more to the region where the turbine blade total pressure loss coefficient is low. And to provide a gas turbine with an increased turbine output.

[0017]

In order to achieve the above object, a gas turbine according to the present invention comprises a turbine stage comprising a combination of a turbine nozzle and a turbine blade, as described in claim 1. In a gas turbine in which turbine stages are arranged in a plurality of stages along the flow of a gas turbine driving gas, when an aspect ratio of the turbine moving blade is 1.5 or less, a cooling medium provided in the turbine nozzle and cooling the inside of the blade At the blade height position 0 in the case where the outlet hole for blowing the air to the outside of the blade is 100% blade height of the turbine nozzle.
It is drilled in the range of 25% and 75-100%.

In order to achieve the above object, a gas turbine according to the present invention comprises a turbine stage formed by combining a turbine nozzle and a turbine rotor blade, and the turbine stage is formed by a gas turbine. In the gas turbine arranged in a plurality of stages along the flow of the turbine driving gas, when the aspect ratio of the turbine blade is 1.5 or less, the turbine nozzle is provided in the turbine nozzle, and the cooling medium after cooling in the blade is outside the blade. Of the outlet holes to be blown, blade height position 0 to 25% when the blade height of the turbine nozzle is 100%
And the opening area of the outflow hole in the range of 75 to 100% is increased, and the opening area of the outflow hole in the range of the blade height position of 25 to 75% is reduced.

According to a third aspect of the present invention, a gas turbine according to the present invention comprises a turbine stage formed by combining a turbine nozzle and a turbine rotor blade. In a gas turbine arranged in multiple stages along the flow of turbine drive gas,
When the aspect ratio of the turbine blade is 1.2 or more,
A blade height position of 25 to 75% in the case where the blade height of the turbine nozzle is set to 100%, and the outlet hole provided in the turbine nozzle and for blowing the cooling medium after cooling in the blade to the outside of the blade is set to 100%.
Are drilled in the range of.

In order to achieve the above object, a gas turbine according to the present invention, as described in claim 4, forms a turbine stage by combining a turbine nozzle and a turbine rotor blade, and forms a turbine stage with a gas. In a gas turbine arranged in multiple stages along the flow of turbine drive gas,
When the aspect ratio of the turbine blade is 1.2 or more,
Of the outlet holes provided in the turbine nozzle and blowing out the cooling medium after cooling inside the blade to the outside of the blade, blade height positions 0 to 25 when the blade height of the turbine nozzle is 100%.
% And the opening area of the outflow holes in the range of 75 to 100%.

According to a fifth aspect of the present invention, there is provided a gas turbine according to the present invention, wherein a turbine stage is formed by combining a turbine nozzle and a turbine rotor blade. In the gas turbine arranged in a plurality of stages along the flow of the gas for driving the gas turbine, when the aspect ratio of the turbine blade is 1.5 or less, the cooling medium provided in the turbine nozzle and cooling the inside of the blade is discharged outside the blade. Outflow holes to be blown into the turbine nozzle at the blade height positions of 0 to 25% and 75 to 100% when the blade height of the turbine nozzle is 100%, and one of the turbine rotor blades The maximum value of the geometric outflow angle obtained from the throat ratio between the throat and the pitch between the rotor blade and the adjacent turbine rotor blade is set within the range of the blade height position of 30 to 65%. It is.

In order to achieve the above object, a gas turbine according to the present invention, as described in claim 6, forms a turbine stage by combining a turbine nozzle and a turbine rotor blade, and forms a turbine stage with a gas. In the gas turbine arranged in a plurality of stages along the flow of the turbine driving gas, when the aspect ratio of the turbine blade is 1.5 or less, the turbine nozzle is provided in the turbine nozzle, and the cooling medium after cooling in the blade is outside the blade. Of the outlet holes to be blown, blade height position 0 to 25% when the blade height of the turbine nozzle is 100%
And the opening area of the outflow hole in the range of 75 to 100% is increased, and the opening area of the outflow hole in the range of the blade height position of 25 to 75% is reduced. The maximum value of the geometrical outflow angle obtained from the throat ratio between the throat and the pitch between the blade and the next turbine blade is set within the range of the blade height position 30 to 65%.

In order to achieve the above object, a gas turbine according to the present invention, as described in claim 7, forms a turbine stage by combining a turbine nozzle and a turbine rotor blade, and forms a turbine stage with a gas turbine. In the gas turbine arranged in a plurality of stages along the flow of the turbine driving gas, when the aspect ratio of the turbine moving blade is 1.2 or more, the turbine blade is provided in the turbine nozzle, and the cooling medium after cooling in the blade is discharged outside the blade. The outlet hole to be blown out is bored in the range of 25 to 75% of the blade height position when the blade height of the turbine nozzle is set to 100%, and one of the turbine blades is adjacent to the turbine blade adjacent to the turbine nozzle. The minimum value of the geometric outflow angle obtained from the throat ratio between the throat with the blade and the pitch is set within the range of the blade height position of 30 to 65%.

Further, in order to achieve the above object, a gas turbine according to the present invention, as described in claim 8, forms a turbine stage by combining a turbine nozzle and a turbine rotor blade, and forms a turbine stage by a gas turbine. In the gas turbine arranged in a plurality of stages along the flow of the turbine driving gas, when the aspect ratio of the turbine moving blade is 1.2 or more, the turbine blade is provided in the turbine nozzle, and the cooling medium after cooling in the blade is discharged outside the blade. Of the outlet holes to be blown, blade height positions 25 to 75 when the blade height of the turbine nozzle is 100%.
%, The opening area of the outlet hole is increased, and the blade height position 0
The opening area of the outflow hole in the range of ２５25% and 75〜100% is reduced, and the throat ratio between the throat and the pitch of one of the turbine moving blades and the adjacent turbine moving blade is determined. The minimum value of the calculated geometrical outflow angle is set within the range of the blade height position 30 to 65%.

[0025]

DESCRIPTION OF THE PREFERRED EMBODIMENTS Embodiments of a gas turbine according to the present invention will be described below with reference to the drawings and reference numerals attached to the drawings.

FIG. 1 shows a first embodiment of the gas turbine according to the present invention.
It is an outline sectional view showing an embodiment.

The gas turbine according to the present embodiment comprises a turbine stage 14 having a turbine nozzle 12 on the upstream side of a gas turbine driving gas (hereinafter, referred to as a main flow) and a turbine rotor blade 13 on the downstream side thereof. This is an axial flow type in which the turbine stages 14 are arranged in a plurality of stages along the main flow direction.

The turbine nozzle 12 has an annular outer ring 1 at the top.
5 is provided with an annular inner ring 16 at the bottom, and an outer ring 15
Are fixed to the casing 16 and are arranged as an annular cascade.

The turbine rotor blades 13 are arranged in a circular cascade with their bottoms planted in a disk-shaped rotor disk 17, and face the heat-insulating segments 19 whose tops are fixed to the casing 8 at a distance. ing.

In the gas turbine having such a configuration,
When a turbine blade 13 having an aspect ratio (ratio of blade height to chord length) of 1.5 or less is implemented, in the present embodiment, the turbines at the top and bottom sides of the turbine blade 13 already described with reference to FIG. Paying attention to the fact that the blade total pressure loss coefficient is low, the outflow holes are provided at the trailing edge in the range of blade height positions 0 to 25% and 75 to 100% when the blade height of the turbine nozzle 12 is 100%. The high-pressure air C after cooling is blown out, and the flow rate to the top and bottom sides of the turbine blade 13 is increased as shown in FIG. In FIG. 4, the dashed line indicates the flow rate distribution to the turbine blade 13 of the conventional combined fluid obtained by adding the main flow to the blade-cooled high-pressure air uniformly flowing out from each blade height position of the turbine nozzle 12 and the solid line. The distribution of the flow rate of the combined fluid of the present embodiment to the turbine blade 13 is shown.

In this embodiment, the throat s and the pitch between one turbine blade 13 and the next turbine blade 13 are adjusted so that the combined fluid flows more at the top and bottom sides of the turbine blade 13. t throat ratio s /
The maximum value of the geometrical outflow angle α = cos ⁻¹ (s / t) obtained from t is set within the range of the blade height position 30 to 65% as shown in FIG. And the geometrical outflow angles α = c on the top and bottom sides
os ^-1 (s / t) is set to be smaller than the conventional value indicated by the broken line.

In FIG. 6, the broken line represents the distribution of the geometrical outflow angle α = cos ⁻¹ (s / t) at each blade height of the conventional turbine blade 13 obtained from the throat ratio s / t. The solid line indicates the distribution of the geometric outflow angle α = cos ⁻¹ (s / t) in the present embodiment.

In the present embodiment, an outflow hole is provided at the trailing edge of the turbine nozzle 12 at the blade height position in the range of 0 to 25% and 75 to 100%, and the geometric outflow angle α = cos ^{− of the} turbine blade 13. ¹ The maximum value of (s / t) is changed to the wing height position 30-6.
It is set within the range of 5%, and the geometric outflow angle α = cos ⁻¹ (s / t) on the top side and the bottom side is made smaller than before so that more combined fluid flows to the turbine blade 13. When,
As shown in FIG. 5, it was recognized that the turbine blade loss was made lower than the conventional loss shown by the broken line. Here, the turbine rotor blade loss is defined as a product of a flow rate flowing through a unit flow path area and a turbine rotor blade total pressure loss coefficient.

As described above, according to the present embodiment, the blade height positions of the turbine nozzle 12 are 0 to 25% and 75 to 100%.
% Range, and the geometric outflow angle α = cos ⁻¹ (s / t) of the turbine blade 13 is set smaller at the top and bottom sides than in the conventional case. Since a larger amount of combined fluid flows in the region having the lower total pressure loss coefficient and the turbine rotor blade loss is reduced as compared with the conventional case, the gas turbine output can be further increased under a high temperature main stream.

FIG. 2 shows a first embodiment of the gas turbine according to the present invention.
It is an outline sectional view showing the modification in an embodiment. The same components as those of the first embodiment are denoted by the same reference numerals.

In this embodiment, when the turbine blade 13 having an aspect ratio of 1.5 or less is used, the blade height positions 0 to 25% and 75 to 100% of the outflow holes provided at the trailing edge of the turbine nozzle 12. To increase the flow of the high-pressure air C after the blade cooling, and to reduce the flow of the high-pressure air C after the blade cooling by reducing the blowing area in the range of blade height 25 to 75%. It is a thing.

In this embodiment, the geometric outflow angle α of the turbine blade 13 is the same as that shown in FIG. 6 of the first embodiment.
= Cos ^-1 (s / t) is set within the range of 30 to 65% of the blade height, and is set to be larger than the conventional value indicated by the broken line, and the top and bottom side geometrical outflow angles are set. α =
cos ^-1 (s / t) is set to be smaller than the conventional value indicated by the broken line.

As described above, in the present embodiment, the opening area of the outflow hole provided at the trailing edge of the turbine nozzle 12 is reduced by the blade height position 0
-25% and 25-75%, and smaller in the blade height position 25-75%, and the geometric outflow angle α = cos ⁻¹ (s / t) of the turbine rotor blade 13 is increased. Since the top side and the bottom side are set to be smaller than those in the related art, as in the case of the first embodiment shown in FIG. 4, more combined fluid can flow in the region where the turbine blade total pressure loss coefficient is low.

Therefore, according to the present embodiment, as shown in FIG. 5 of the first embodiment, the turbine blade loss can be reduced as compared with the prior art, and under the high temperature of the mainstream,
The gas turbine output can be further increased.

FIG. 7 shows a second embodiment of the gas turbine according to the present invention.
It is an outline sectional view showing an embodiment. The same components as those of the first embodiment are denoted by the same reference numerals.

In this embodiment, when the turbine blade 13 having an aspect ratio of 1.2 or more is implemented, the turbine nozzle 12
An outlet hole is provided in the range of 25 to 75% of the wing height position of the trailing edge,
The high-pressure air after blade cooling from the blade height position in the range of 25 to 75% flows out to the turbine blade 13.

In general, when a turbine blade 13 having an aspect ratio of 1.2 or more is used in a gas turbine, as shown in FIG. 9, the blade height position of the turbine blade 13 ranges from 0 to 25% and 75 to 100%. , The turbine blade total pressure loss coefficient is high, and the turbine blade total pressure loss coefficient is low in the range of blade height 25 to 75%.

In this embodiment, when the turbine blade 13 having an aspect ratio of 1.2 or more is implemented, attention is paid to the point that the turbine blade total pressure loss coefficient is low at the middle portion of the blade height of the turbine blade 13 and the turbine nozzle An outflow hole is provided at the trailing edge of the blade height position 25 to 75% in the range of 12 to generate high-pressure air c after blade cooling, and the flow rate of the turbine rotor blade 13 to the blade height intermediate portion is shown in FIG. It is increased as follows. FIG.
0, the broken line indicates the flow rate distribution of the conventional combined fluid to the turbine rotor blade 13 in which the main flow is added to the high-pressure air after the blade cooling, which uniformly flows out from each blade height position of the turbine nozzle 12, and the solid line indicates the present embodiment. 2 shows the flow distribution of the combined fluid to the turbine rotor blades 13.

Further, in the present embodiment, the geometric outflow angle α = cos ⁻¹ (s / t) of the turbine blade 13 is minimized so that the combined fluid flows more in the middle portion of the blade height of the turbine blade 13. The value is set within the range of 30 to 65% of the blade height position as shown in FIG. 12 and is made smaller than the conventional one shown by the broken line, and the geometrical outflow angle α on the top side and the bottom side is set.
= Cos ^-1 (s / t) is set to be larger than the conventional value indicated by the broken line. In FIG. 12, a broken line indicates a geometric outflow angle α at each blade height position of the conventional turbine blade 13.
The distribution of cos ^-1 (s / t) and the solid line show the distribution of the geometric outflow angle α = cos ^-1 (s / t) in the present embodiment.

In this embodiment, an outflow hole is provided at the trailing edge of the blade height position of 25 to 75% of the turbine nozzle 12, and the geometric outflow angle α = cos ⁻¹ (s / t) of the turbine rotor blade 13 is provided.
Is set within the range of the blade height position of 30 to 65%, and the geometrical outflow angles α = cos ⁻¹ (s
/ T) is made larger than before, and the combined fluid is
As shown in FIG. 11, it was recognized that the turbine blade loss was made lower than the conventional loss shown by the broken line when more flow was made to flow to the blade height middle portion of FIG.

As described above, according to the present embodiment, when the turbine blade having the aspect ratio of 1.2 or more is implemented, the outflow hole is provided at the trailing edge of the turbine nozzle 12 in the blade height position range of 25 to 75%. , The minimum value of the geometric outflow angle α = cos ⁻¹ (s / t) of the turbine rotor blade 13 is set to the blade height position 30 to 6
It was set within the range of 5%, and more combined fluid flowed to the region where the turbine blade total pressure loss coefficient was low, and the turbine blade loss was reduced as compared with the conventional one.
The gas turbine output can be further increased.

FIG. 8 shows a second embodiment of the gas turbine according to the present invention.
It is an outline sectional view showing the modification in an embodiment. The same components as those of the first embodiment are denoted by the same reference numerals.

In this embodiment, when the turbine moving blade 13 having an aspect ratio of 1.2 or more is used, of the outlet holes provided at the trailing edge of the turbine nozzle 12, the blowout area in the range of 25 to 75% of the blade height position. To increase the flow of the high-pressure air c after the blade cooling, and reduce the blowing area in the range of 0 to 25% and 75 to 100% of the blade height position to reduce the flow of the high-pressure air after the blade cooling. It was made.

This embodiment is different from the second embodiment shown in FIG.
Similarly, the minimum value of the geometric outflow angle α = cos ⁻¹ (s / t) of the turbine rotor blade 13 is set within the range of the blade height of 30 to 65%, and is compared with the conventional one shown by the broken line. And the geometrical outflow angles α on the top and bottom sides
= Cos ^-1 (s / t) is set to be larger than the conventional value indicated by the broken line.

As described above, in this embodiment, the opening area of the outflow hole provided at the trailing edge of the turbine nozzle 12 is reduced by the blade height position 25.
To 75% of the blade height position and to a small value in the range of 75 to 100% of the blade height position, and the geometric outflow angle α = cos ⁻¹ (s / t) of the turbine rotor blade 13. Since the minimum value is set within the range of the blade height of 30 to 65%, which is smaller than the conventional value, as shown in FIG. 10 of the second embodiment, the minimum value is more in the region where the turbine blade total pressure loss coefficient is lower. Can flow.

Therefore, according to the present embodiment, similarly to the second embodiment shown in FIG. 11, the turbine blade loss can be reduced as compared with the conventional case, and the gas turbine output can be reduced under the high temperature of the mainstream. Can be further increased.

[0052]

As described above, in the gas turbine according to the present invention, when a turbine blade having an aspect ratio of 1.5 or less is implemented, more mainstream gas flows in the region where the turbine blade total pressure loss coefficient is low. Outflow holes are provided at the top of the turbine nozzle at the top of the blade height and at the bottom of the blade at the top of the blade so that the combined fluid flows with the high-pressure air after cooling the blades. , The turbine blade loss can be reduced, and the gas turbine output can be increased.

Further, in the gas turbine according to the present invention, when a turbine blade having an aspect ratio of 1.2 or more is implemented, more main flow and high-pressure air after blade cooling are provided in the region where the turbine blade total pressure loss coefficient is low. An outlet hole is provided at the midpoint of the blade height of the turbine nozzle so that the combined fluid flows, and the outflow angle at the midpoint of the blade height of the turbine blade is set smaller than before, so the turbine blade loss Can be reduced, and the output of the gas turbine can be increased.

[Brief description of the drawings]

FIG. 1 is a schematic sectional view showing a first embodiment of a gas turbine according to the present invention.

FIG. 2 is a schematic sectional view showing a modification of the first embodiment of the gas turbine according to the present invention.

FIG. 3 is a diagram showing a conventional turbine blade total pressure loss coefficient distribution when a turbine blade having an aspect ratio of 1.5 or less is implemented.

FIG. 4 is a diagram comparing distribution of a combined fluid in the first embodiment of the gas turbine according to the present invention with distribution of a conventional combined fluid.

FIG. 5 is a diagram comparing the distribution of turbine blade loss in the first embodiment of the gas turbine according to the present invention with the distribution of turbine blade loss in the related art.

FIG. 6 is a diagram comparing the distribution of the geometric outflow angle of the turbine blade in the first embodiment of the gas turbine according to the present invention with the distribution of the geometric outflow angle of the conventional turbine blade.

FIG. 7 is a schematic sectional view showing a second embodiment of the gas turbine according to the present invention.

FIG. 8 is a schematic sectional view showing a modification of the second embodiment of the gas turbine according to the present invention.

FIG. 9 is a diagram showing a conventional turbine blade total pressure loss coefficient distribution when a turbine blade having an aspect ratio of 1.2 or more is implemented.

FIG. 10 is a diagram comparing distribution of a combined fluid in the second embodiment of the gas turbine according to the present invention with distribution of a conventional combined fluid.

FIG. 11 is a diagram comparing the distribution of turbine blade loss in the second embodiment of the gas turbine according to the present invention with the distribution of turbine blade loss in the related art.

FIG. 12 is a diagram comparing the distribution of the geometric outflow angle of the turbine blade in the second embodiment of the gas turbine according to the present invention with the distribution of the geometric outflow angle of the conventional turbine blade.

FIG. 13 is a schematic diagram illustrating a loss due to a secondary flow generated in a turbine nozzle.

FIG. 14 is a schematic view showing a conventional turbine nozzle.

FIG. 15 is a diagram showing a conventional distribution of turbine nozzle loss.

[Explanation of symbols]

 1a, 1b Turbine nozzle 2a, 2b Trailing edge 3a, 3b Outflow hole 4a, 4b Front edge 5a, 5b Backside 6a, 6b Outflow hole 7 Flow path 8 Dimensional flow 9 Outer ring wall 10 Inner ring wall 11 Flow path vortex 12 Turbine nozzle 13 Turbine rotor blade 14 Turbine stage 15 Outer ring 16 Inner ring 17 Rotor disk 18 Casing 19 Heat insulation segment

Claims (8)

[Claims] In a gas turbine in which a turbine stage is formed by combining a turbine nozzle and a turbine blade, and the turbine stage is arranged in a plurality of stages along the flow of a gas turbine driving gas, the aspect ratio of the turbine blade is reduced. 1.
5 or less, the outlet holes provided in the turbine nozzle for blowing the cooling medium after cooling in the blade to the outside of the blade are located at blade height positions 0 to 25% and 75 when the blade height of the turbine nozzle is 100%. A gas turbine characterized by being drilled in the range of 100% to 100%. 2. A gas turbine in which a turbine stage is formed by combining a turbine nozzle and a turbine blade, and the turbine stage is arranged in a plurality of stages along the flow of a gas turbine driving gas. 1.
5 or less, among the outlet holes provided in the turbine nozzle for blowing out the cooling medium after cooling inside the blade to the outside of the blade, the blade height positions 0 to 25% when the blade height of the turbine nozzle is 100%, and A gas turbine wherein the opening area of the outflow hole in the range of 75 to 100% is increased, and the opening area of the outflow hole in the range of the blade height position of 25 to 75% is reduced. 3. A gas turbine in which a turbine stage is formed by combining a turbine nozzle and a turbine rotor blade, and the turbine rotor blades are arranged in a plurality of stages along the flow of a gas turbine driving gas. In the case of 1.2 or more, the outlet hole provided in the turbine nozzle for blowing out the cooling medium after cooling inside the blade to the outside of the blade is located at a blade height position of 25 to 75% when the blade height of the turbine nozzle is 100%. A gas turbine characterized by being drilled in the range of. 4. A gas turbine in which a turbine stage is formed by combining a turbine nozzle and a turbine rotor blade, and the turbine rotor blade is arranged in a plurality of stages along the flow of a gas turbine driving gas. 1.2 or more, among the outlet holes provided in the turbine nozzle and blowing out the cooling medium after cooling inside the blade to the outside of the blade, blade height positions 0 to 25 when the blade height of the turbine nozzle is 100%. % And the opening area of the outflow hole in the range of 75 to 100% is reduced. 5. A gas turbine in which a turbine stage is formed by combining a turbine nozzle and a turbine blade, and the turbine stage is arranged in a plurality of stages along the flow of a gas turbine driving gas. Is 1.
5 or less, the outlet holes provided in the turbine nozzle for blowing the cooling medium after cooling in the blade to the outside of the blade are located at blade height positions 0 to 25% and 75 when the blade height of the turbine nozzle is 100%. And a maximum value of a geometric outflow angle obtained from a throat ratio between a throat and a pitch of one of the turbine moving blades and an adjacent turbine moving blade. The gas turbine is characterized in that the height is set within a range of a blade height position of 30 to 65%. 6. In a gas turbine in which a turbine stage is formed by combining a turbine nozzle and a turbine blade, and the turbine stage is arranged in a plurality of stages along the flow of a gas turbine driving gas, the aspect ratio of the turbine blade is reduced. 1.
5 or less, among the outlet holes provided in the turbine nozzle and blowing out the cooling medium after cooling in the blade to the outside of the blade, the blade height positions 0 to 25% when the blade height of the turbine nozzle is 100%, and The opening area of the outflow hole in the range of 75 to 100% is increased, the opening area of the outflow hole in the range of the blade height position of 25 to 75% is reduced, and one of the turbine blades is connected to the turbine blade. A gas turbine wherein a maximum value of a geometric outflow angle obtained from a throat ratio between a throat and a pitch with an adjacent turbine rotor blade is set within a range of a blade height position of 30 to 65%. 7. A gas turbine in which a turbine stage is formed by combining a turbine nozzle and a turbine rotor blade, and the turbine rotor blade is arranged in a plurality of stages along the flow of a gas turbine driving gas. 1.
In the case of 2 or more, the outlet hole provided in the turbine nozzle and for blowing the cooling medium after cooling the inside of the blade to the outside of the blade has a blade height position of 25 to 75% when the blade height of the turbine nozzle is 100%. And the minimum value of the geometrical outflow angle determined from the throat ratio between the throat and the pitch of one of the turbine blades and the next turbine blade is set in the blade height position 30 to A gas turbine characterized by being set within a range of 65%. 8. A gas turbine in which a turbine stage is formed by combining a turbine nozzle and a turbine blade, and the turbine stage is arranged in a plurality of stages along the flow of a gas turbine driving gas. 1.
In the case of 2 or more, of the outlet holes provided in the turbine nozzle and for blowing the cooling medium after cooling inside the blade to the outside of the blade, the blade height position of 25 to 75% when the blade height of the turbine nozzle is 100%. The opening area of the outflow hole in the range is increased, and the opening area of the outflow hole in the range of the blade height positions 0 to 25% and 75 to 100% is reduced. A gas turbine wherein a minimum value of a geometric outflow angle obtained from a throat ratio between a throat and a pitch with an adjacent turbine blade is set within a range of a blade height position of 30 to 65%.