JP2010190057A - Design method of turbine and turbine - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To reduce heat loads to stationary blades of stationary blade lines arranged in a downstream region of moving blade lines in a turbine in which a plurality of stationary blade lines and moving blade lines are alternately arranged in a flowing direction of a fluid. <P>SOLUTION: Stationary blades 52 of stationary blade lines 62 arranged in a downstream region of moving blade lines 71 are arranged so as to avoid a hot streak H. <P>COPYRIGHT: (C)2010,JPO&amp;INPIT

Description

  The present invention relates to a turbine design method and a turbine in which a plurality of stationary blade rows and moving blade rows are alternately arranged in a fluid flow direction.

Conventionally, in an apparatus including a turbine that is rotationally driven by a high-temperature fluid such as a gas turbine engine, the high-temperature fluid is supplied to the turbine.
Particularly, since the fuel injection nozzles installed in the combustor are discretely arranged on the downstream side of the combustor included in the gas turbine engine, a high-temperature fluid flows locally. Therefore, so-called hot streaks extending in the fluid flow direction are discretely formed in the circumferential direction in the downstream region of the combustor. And when the blade | wing with which a turbine is exposed to a hot streak, the thermal load of a turbine blade especially becomes large.

For this reason, in the conventional gas turbine engine etc., in order to suppress the occurrence of the hot streak, an attempt has been made to eliminate the hot streak by appropriately mixing the diluted air in the combustor.
However, the heat flow inside the combustor is very complex and difficult to predict. For this reason, even if dilution air is mixed in order to suppress the occurrence of hot streaks, the target temperature distribution is not always achieved.

In view of this, attempts have been made not to take measures for hot streaks in the combustor or to simplify measures and to take measures against heat in the turbine.
Specifically, for example, a cooling gas that can withstand hot streak is supplied to the inside of the stationary blade that is the turbine blade closest to the combustor, and the stationary blade is cooled to reduce the thermal load on the stationary blade. ing.

JP 2004-257390 A

  However, the hot streak is not attenuated and dissipated in a stationary blade row composed of a plurality of stationary blades and a moving blade row arranged in a downstream region of the stationary blade row, and remains further downstream.

For this reason, in a multi-stage turbine including a plurality of cascade stages composed of a stationary cascade and a moving cascade, the stationary blades constituting the stationary cascade arranged downstream of the stationary cascade are exposed to hot streak and generate a large amount of heat. There may be a load.
On the other hand, it is conceivable to supply all the stationary blades with cooling gas that can withstand hot streak inside, but the cooling air increases so much that the engine performance is significantly reduced.

  The present invention has been made in view of the above-described problems, and in a turbine in which a plurality of stationary blade rows and moving blade rows are alternately arranged in the fluid flow direction, the static blade disposed in the downstream region of the moving blade row. The purpose is to reduce the thermal load on the stationary blades of the cascade.

  The following configuration is adopted as means for solving the above-described problems.

  A first invention is a turbine design method in which a plurality of stationary blade rows and moving blade rows are alternately arranged in a fluid flow direction, and obtains a temperature distribution in a downstream region of the moving blade row. And a stationary blade arrangement position setting step of setting a region having a temperature lower than a predetermined threshold in the temperature distribution acquired in the temperature distribution acquisition step as a stationary blade arrangement position of the stationary blade row. The configuration is adopted.

  According to a second invention, in the first invention, in the temperature distribution acquisition step, the temperature distribution is acquired by calculating a hot streak distribution in a downstream region of the blade row by fluid analysis. To do.

  According to a third invention, in the first or second invention, in the temperature distribution acquisition step, the temperature distribution is acquired by calculating a cold streak distribution in a downstream region of the moving blade row by fluid analysis. Adopt the configuration.

  According to a fourth invention, in any one of the first to third inventions, the stationary blade arrangement position is obtained by performing a fluid analysis based on the arrangement position of the stationary blade set after the stationary blade arrangement position setting step. A verification process for verifying the stator blade arrangement position set after the setting process, and adjusting the stator blade arrangement position set after the stator blade arrangement position setting process based on the verification result of the verification process The adjustment process is employed.

  According to a fifth invention, in any of the first to fourth inventions, in the stationary blade arrangement position setting step, when there are a plurality of stationary blade arrangement positions, the temperature gradient of the stationary blade is the smallest. A configuration is adopted in which the stationary blade arrangement position is selected as the optimum one.

  A sixth invention is a turbine in which a plurality of stationary blade rows and moving blade rows are alternately arranged in a fluid flow direction, and the stationary blades of the stationary blade row arranged in a downstream region of the moving blade row include: A configuration is adopted in which they are arranged outside a region having a temperature higher than a preset threshold value.

  According to a seventh invention, in the sixth invention, the stationary blades of the stationary blade row arranged in the downstream region of the moving blade row are arranged so as to be located in a region lower in temperature than a preset threshold value. Adopt the configuration that.

According to the present invention, the stationary blades of the stationary blade row arranged in the downstream region of the moving blade row of the turbine are arranged so as to avoid hot streak.
Therefore, in a turbine in which a plurality of stationary blade rows and moving blade rows are alternately arranged in the fluid flow direction, it is possible to reduce the thermal load on the stationary blades of the stationary blade rows arranged in the downstream region of the moving blade row. It becomes possible.

It is a mimetic diagram showing the important section composition of the gas turbine engine provided with the turbine in one embodiment of the present invention. It is the schematic diagram which looked at the stationary blade and the moving blade with which the turbine in one Embodiment of this invention is provided from the side. It is a system block diagram of the design apparatus used for the design of the turbine in one Embodiment of this invention. It is a flowchart for demonstrating the design method of the turbine in one Embodiment of this invention.

Hereinafter, an embodiment of a turbine blade design method and a turbine according to the present invention will be described with reference to the drawings.
In the following drawings, the scale of each member is appropriately changed in order to make each member a recognizable size.

FIG. 1 is a cross-sectional view illustrating a configuration of a main part of a high temperature part of a gas turbine engine in which the turbine of the present embodiment is installed.
As shown in this figure, the gas turbine engine includes a combustor 4 and a turbine 5.

  The combustor 4 mixes and burns fuel with compressed air, and discharges combustion gas. A plurality of fuel injection nozzles 2 are discretely arranged around the axis of the gas turbine engine inside the combustor 4, and the fuel and air injected from the fuel injection burner are mixed and burned. The

The turbine 5 obtains rotational power from combustion gas supplied from the combustor 4, and includes turbine blades 51 including a plurality of stationary blades 52 and a plurality of moving blades 53.
FIG. 2 is a schematic view of the stationary blade 52 and the moving blade 53 provided in the turbine 5 as viewed from the side. As shown in this figure, the turbine 5 of the present embodiment includes blades composed of a stationary blade row 60 (61, 62) including the stationary blades 52 and a moving blade row 70 (71, 72) including the blades 53. The row stage 80 has a configuration in which two stages are arranged in the flow direction of the combustion gas. That is, the stationary blade rows 60 and the moving blade rows 70 are alternately arranged in the flow direction of the combustion gas.
In addition, as shown in FIG. 2, the cooling gas X is supplied to the inside of the stationary blade 52 of the upstream stationary blade row 61, and the cooling gas X is supplied to the outside of the stationary blade 52 from the blade surface and the trailing edge of the stationary blade 52. Has been discharged.

In the turbine 5 of the present embodiment, as shown in FIG. 2, the stationary blade 52 of the stationary blade row 62 arranged in the downstream region of the moving blade row 71 of the upstream blade row stage 81 causes the combustion gas flow. The hot streak H that is a high-temperature flow included in the area is formed so as to avoid the region. In this embodiment, the hot streak is a temperature region higher than a preset threshold value, and in this embodiment, avoiding a hot streak means being located outside the temperature region higher than the preset threshold value. To do.
Furthermore, in the turbine 5 of the present embodiment, the cold streak C formed by the cooling gas X is formed in the stationary blade 52 of the stationary blade row 62 arranged in the downstream region of the moving blade row 71 of the upstream blade row stage 81. It arrange | positions so that it may be exposed to the area | region in which (the low temperature flow contained in a combustion gas flow) is formed. In this embodiment, the cold streak is a temperature region lower than a preset threshold value, and in this embodiment, being exposed to a cold streak means being located in a temperature region lower than a preset threshold value. .
Note that the threshold value for defining hot streak and the threshold value for defining cold streak need not be the same value.

  In the gas turbine engine 1 including the turbine 5 of this embodiment having such a configuration, the combustion gas generated in the combustor 4 is supplied to the turbine 5 to obtain rotational power.

  And in the turbine 5 of this embodiment, the stationary blade 52 of the stationary blade row | line | column 62 arrange | positioned in the downstream area | region of the moving blade row | line 71 of the upstream blade row stage 81 is a high temperature flow contained in a combustion gas flow. It is arranged avoiding the hot streak H. For this reason, it is possible to reduce the thermal load on the stationary blade 52 of the stationary blade row 62 arranged in the downstream region of the moving blade row 71.

  Further, in the turbine 5 of the present embodiment, the cold streak C formed by the cooling gas X is formed in the stationary blade 52 of the stationary blade row 62 arranged in the downstream region of the moving blade row 71 of the upstream blade row stage 81. It is arranged to be exposed to. For this reason, it is possible to further reduce the thermal load on the stationary blade 52 of the stationary blade row 62 disposed in the downstream region of the moving blade row 71.

  FIG. 3 is a system block diagram of the design apparatus S for designing the turbine 5. FIG. 4 is a flowchart for explaining a method for designing the turbine 5.

  The design apparatus S is embodied by a personal computer or a workstation. As shown in FIG. 3, the design apparatus S includes an external storage device 100, an internal storage device 200, a CPU 300, an input device 400, and an output device 500. The system bus 600 is provided.

The external storage device 100 is embodied by a hard disk drive or the like. In the present embodiment, the analysis program for calculating the hot streak distribution described above, the stationary blade row 62 of the blade row stage 82 in the downstream region described above, and the like. An arrangement position setting program or the like for setting the arrangement position is stored.
The external storage device 100 also includes parameters used for the analysis program and the arrangement position setting program (data indicating the arrangement interval of the combustion injection valves in the combustor 4, data indicating the amount of heat of the fuel used in the combustor 4, upstream side Data indicating the shape and arrangement interval of the stationary blade 52 in the blade row stage 81, data indicating the shape, arrangement interval and rotation speed of the moving blade 53 in the upstream blade row stage 81, and static data in the downstream blade row stage 82. The data indicating the shape and arrangement interval of the blades 52 are stored. The parameters used for the analysis program and the arrangement position setting program do not necessarily have to be stored in advance in the external storage device 100, but may be input to the input device 400 and stored in the internal storage device 200. .

  The internal storage device 200 is embodied by a ROM, a RAM, or the like. In the present embodiment, the internal storage device 200 temporarily stores the analysis program, the arrangement position setting program, and the parameters used for these programs.

  The CPU 300 controls the entire operation of the design apparatus S. In the present embodiment, the temperature in the downstream region of the moving blade row 71 is based on the analysis program, the arrangement position setting program, and the parameters used in these programs. The distribution is calculated, and the arrangement position of the stationary blades of the stationary blade row 62 is set based on the temperature distribution.

The input device 400 is embodied by a keyboard and a mouse, and inputs parameters used for an analysis program and an arrangement position setting program as necessary.
The output device 500 is embodied by a display or a printer, and visualizes and outputs various data under the control of the CPU 300.
The system bus 600 is a wiring network that electrically connects the external storage device 100, the internal storage device 200, the CPU 300, the input device 400, and the output device 500 to each other.

In the turbine design method of the present embodiment performed using the design apparatus S configured as described above, a temperature distribution acquisition step (step S1) is first performed as shown in FIG. In this temperature distribution acquisition step, the temperature distribution in the downstream region of the moving blade row 71 is calculated based on the analysis program and parameters.
In the turbine design method of the present embodiment, the temperature distribution in the downstream region of the moving blade row 71 is obtained by calculating the distribution of hot streaks and cold streaks using an unsteady CFD analysis program as an analysis program. .
In addition, specific methods for performing unsteady CFD analysis are described in “Hirai, K., et al.,“ Unsteady Three-Dimensional Analysis of Inlet Distortion in Turbomachinery ”, AIAA Paper AIAA-1997-2735. The description here is omitted. The distribution of hot streaks and cold streaks can be calculated using a program (unsteady CFD analysis program) and parameters applying a specific method for performing the unsteady CFD analysis.

Subsequently, in the turbine design method of the present embodiment, a stationary blade arrangement position setting step (step S2) is performed. In the stationary blade arrangement position setting step, the arrangement position of the stationary blades 52 constituting the stationary blade row 62 arranged in the downstream region of the moving blade row 71 is set based on the arrangement position setting program and the parameters.
The number and spacing of the stationary blades 52 constituting the stationary blade row 62 are determined depending on the performance required for the turbine and cannot be changed. For this reason, the arrangement position of the stationary blade 52 which comprises the stationary blade row | line | column 62 is set by changing the attachment rotation angle in the circumferential direction of the stationary blade row | line | column 62 seen from the flow direction of the combustion gas flow.

  In the stationary blade arrangement position setting step, the stationary blade row 62 is avoided so as to avoid the hot streak and be exposed to the cold streak based on the temperature distribution in the downstream region of the moving blade row 71 obtained in the temperature distribution obtaining step. The arrangement position of the stationary blade 52 which comprises is set.

In addition, in the downstream area of the moving blade row 71, the arrangement position of the stationary blade 52 that avoids the hot streak and is exposed to the cold streak is not necessarily one. Therefore, in the turbine design method of the present embodiment, the CPU 300 selects an optimum one from the arrangement positions of the plurality of stationary blades 52 in the stationary blade arrangement position setting step.
Specifically, for example, the CPU 300 calculates a temperature distribution by calculating a hot streak, performs a heat transfer analysis of the stationary blade 52 with the temperature distribution, further calculates a cold streak to obtain a temperature distribution, As a boundary condition, heat transfer analysis of the stationary blade 52 is performed. As a result of the heat transfer analysis, an arrangement position having a small temperature gradient of the stationary blade 52 constituting the stationary blade row 62 is selected and selected as an optimum one.
Further, the CPU 300 selects, for example, an arrangement position where the average temperature is equal to or lower than an allowable value or where there is no local high temperature portion on the stationary blade 52. Further, the CPU 300 executes a stress analysis of the stationary blade 52 at each of the selected stationary blade 52 placement positions, and sets the one having the smallest average stress or maximum stress as the final placement position.

As shown in FIG. 4, after the arrangement position setting step, the unsteady CFD analysis is performed again using the unsteady CFD analysis program, the distribution of hot streaks and cold streaks is calculated, and the downstream region of the moving blade row 71 It is preferable to perform a verification process (step S3) for verifying whether the stationary blades 52 of the stationary blade row 62 are optimally arranged so as to avoid hot streaks and to be exposed to cold streaks.
Here, when it is determined that the stationary blade 52 is not optimally arranged, an adjustment process for adjusting the arrangement position of the stationary blade 52 is performed until it is determined to be optimal in the verification process (step S4).

According to the turbine design method of the present embodiment as described above, the stationary blade 52 provided in the stationary blade row 62 disposed in the downstream region of the moving blade row 71 is exposed to the cold streak C while avoiding hot streak. It is possible to design a turbine arranged in
Therefore, it is possible to design a turbine capable of reducing the thermal load on the stationary blade 52 of the stationary blade row 62 arranged in the downstream region of the moving blade row 71.

  As mentioned above, although preferred embodiment of this invention was described referring drawings, this invention is not limited to the said embodiment. Various shapes, combinations, and the like of the constituent members shown in the above-described embodiments are examples, and various modifications can be made based on design requirements and the like without departing from the gist of the present invention.

For example, in the above-described embodiment, the configuration in which the distribution of both hot streaks and cold streaks is calculated to obtain the temperature distribution in the downstream region of the moving blade row 71 has been described.
However, the present invention is not limited to this, and the temperature distribution in the downstream region of the rotor blade row 71 may be obtained using only hot streaks or cold streaks.
Even in such a case, since the hot streak is a region where the temperature is higher than a predetermined threshold and the cold streak is a region where the temperature is lower than a predetermined threshold, the arrangement position of the stationary blade 52 is determined in advance. It is possible to set a region where the temperature is lower than a predetermined threshold value while avoiding a region where the temperature is higher than the predetermined threshold value.

In the above-described embodiment, the configuration has been described in which the temperature distribution in the downstream region of the moving blade row 71 is obtained by calculating the distribution of hot streaks and cold streaks using unsteady CFD analysis.
However, the present invention is not limited to this. For example, the temperature distribution in the downstream region of the moving blade row 71 may be acquired using a temperature measuring device such as a thermocouple.

Moreover, in the said embodiment, the structure by which the stationary blade row | line | column 60 and the moving blade row | line | column 70 were alternately arrange | positioned 2 each was demonstrated, ie, the structure by which the two blade row | line | column stage 80 was arrange | positioned.
However, the present invention is not limited to this, and a configuration including a plurality of blade rows can also be adopted. For example, the arrangement position of the vanes 52 of the third and subsequent blade rows 60 is set. In particular, it can be applied.

Further, in the above-described embodiment, the example in which the blade row stage is configured by one stationary blade row 60 and one moving blade row 70 has been described.
However, the present invention is not limited to this, and the cascade stage may be configured by different numbers of stationary blade arrays and moving blade arrays such as two stationary blade arrays and one moving blade array.
Even in such a case, the arrangement position of the stationary blades of the stationary blade row arranged in the downstream region of the moving blade row can be set by the present invention.

Moreover, in the said embodiment, the turbine with which a gas turbine engine is equipped, and the design method of this turbine were demonstrated.
However, this invention is not limited to this, For example, it is also possible to apply to the turbine used for a steam turbine generator etc.

  5 ... Turbine, 52 ... Stator blade, 53 ... Rotor blade, 60 (61, 62) ... Stator blade row, 70 (71, 72) ... Rotor blade row, 80 ... Blade row stage, H ... ... hot streak, C ... cold streak

Claims (7)

A turbine design method in which a plurality of stationary blade rows and moving blade rows are alternately arranged in a fluid flow direction,
A temperature distribution acquisition step of acquiring a temperature distribution in a downstream region of the blade row;
A stationary blade arrangement position setting step of setting a region having a temperature lower than a predetermined threshold in the temperature distribution acquired in the temperature distribution acquisition step as a stationary blade arrangement position of the stationary blade row. The turbine design method.   2. The turbine design method according to claim 1, wherein, in the temperature distribution acquisition step, the temperature distribution is acquired by calculating a hot streak distribution in a downstream region of the moving blade row by fluid analysis.   3. The turbine design method according to claim 1, wherein in the temperature distribution acquisition step, the temperature distribution is acquired by calculating a cold streak distribution in a downstream region of the moving blade row by fluid analysis. Verification for verifying the stationary blade arrangement position set after the stationary blade arrangement position setting step by performing fluid analysis based on the stationary blade arrangement position set after the stationary blade arrangement position setting step Process,
The adjustment step of adjusting the arrangement position of the stationary blade set after the stationary blade arrangement position setting step based on the verification result of the verification step, Turbine design method.   In the stationary blade arrangement position setting step, when there are a plurality of stationary blade arrangement positions, the stationary blade arrangement position having the smallest temperature gradient of the stationary blade is selected as an optimum one. Item 5. A turbine design method according to any one of Items 1 to 4. A turbine in which a plurality of stationary blade rows and moving blade rows are alternately arranged in a fluid flow direction,
The turbine according to claim 1, wherein the stationary blades of the stationary blade row arranged in the downstream region of the moving blade row are arranged outside a region having a temperature higher than a preset threshold value.   The turbine according to claim 6, wherein the stationary blades of the stationary blade row arranged in the downstream region of the moving blade row are arranged so as to be located in a region where the temperature is lower than a preset threshold value. .

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