JP2014202090A - Cooling structure in turbine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a cooling structure in a turbine, which requires a limited space and can effectively cool a turbine without using cooling methods such as film cooling and hollow cooling.SOLUTION: A cooling structure of a turbine requires a limited space, and can effectively cool the turbine without film cooling or hollow cooling with cooling air. That is, a high temperature vaporizing object injection part provided on a stationary part side can cool a turbine rotation part by jetting and applying a high temperature vaporizing object to turbine rotation parts, such as a moving blade, a rotation shaft or a turbine disk, and vaporizing it at a predetermined high temperature or higher. As the high temperature vaporizing object, for example, an ablation material can be used.

Description

  The present invention relates to a cooling structure in a turbine, and more particularly to a cooling structure in a turbine in which the strength of the turbine blade is maintained by cooling with respect to a turbine blade used in a high temperature environment.

For example, in axial flow turbines such as gas turbines, so-called partial feed turbines are the mainstream for higher efficiency.
The partial feeding turbine is a first stage nozzle that partially feeds the working fluid by providing a working fluid feeding part and a non-feeding part in the circumferential direction, a cavity disposed downstream of the nozzle, And a one-stage nozzle.
In such a structure, the working fluid is introduced through the feeding section, so that the operable efficiency is ensured regardless of the increase or decrease of the working fluid.
Further, in the turbine, for example, ensuring the heat resistance and strength of the turbine used in a high temperature environment such as an underwater machine is an important issue as well as increasing the efficiency of the turbine. That is, in the turbine, since the high temperature of the turbine inlet contributes to the improvement of thermal efficiency, cooling of high-temperature members such as turbine blades and combustors has become an indispensable technical issue from the viewpoint of improving performance.
Here, as cooling means for turbine blades, in order to increase cooling efficiency, convection cooling, impingement cooling, pin fin cooling, full surface film cooling, etc. have been proposed, and the structure is refined and a high cooling called a transpiration cooling structure. Aiming for performance.

  For example, Patent Document 1 discloses an air-cooled gas turbine turbine blade as a gas turbine cooling technique. That is, in Patent Document 1, a cooling flow path that feeds cooling air from the center of the rotor is formed in the turbine blades, and a flow of introducing a part of the cooling air that has flowed through the flow path and increased in temperature into the intermediate chamber. An exit is provided.

  On the other hand, the applicant has a series of cylindrical air passages formed between the air separator and the rotor, and between the air separator and the disk, as in Patent Document 2, via the air passage. In a cooling apparatus for gas turbine turbine blades for introducing air for cooling turbine blades, an annular convex portion provided on the outer surface of a rotor or a disk constituting the inner wall of the flow path so as to protrude radially outward, and an outer wall of the flow path An annular recess provided so as to cover the annular projection via a gap serving as an air flow path at a position facing the annular projection on the inner surface of the air separator, and one end connected to the bottom of the annular recess and the other end It is set as the structure provided with the several through-hole connected with the air separator outer peripheral side space.

Japanese Patent Publication No. 63-64601 Japanese Patent No. 3160484

Since both of the above Patent Documents 1 and 2 are based on the premise that the cooling air can be freely taken in, for example, in an underwater vehicle that travels underwater, the installation space is limited. Therefore, a cooling technique such as film cooling using cooling air and hollow cooling, such as the above-described gas turbine, cannot be applied.
The present invention has been proposed from the background as described above, and in a turbine capable of effectively cooling a turbine in a limited space without using cooling methods such as film cooling and hollow cooling. An object is to provide a cooling structure.

  In order to solve the above-mentioned problems, according to the present invention, a cooling structure in a turbine that cools a turbine rotating part with respect to a turbine that is operated by a working fluid, It is characterized by comprising a high-temperature vapor injection unit that vaporizes the high-temperature vaporized product by injecting the vapor and cools the turbine rotating unit.

  As a result, when high-temperature vaporized material is injected from the high-temperature vaporized material injection unit to the high-temperature turbine rotating unit, the high-temperature vaporized material injected on the surface of the high-temperature turbine rotating unit is vaporized at high temperature and vaporized. The turbine rotating part can be cooled by heat.

  Further, in the present invention described in claim 2, the turbine rotating part includes a rotating shaft, a turbine disk, and a moving blade.

  As a result, the rotating shaft, the turbine disk, and the moving blades are brought into direct contact with each other by feeding a working fluid to increase the temperature, so that high temperature vaporized material is injected onto the rotating shaft, the turbine disk, and the moving blade surfaces. Thus, the injected high-temperature vaporized material is vaporized, and the rotating shaft, the turbine disk, and the rotor blade can be cooled.

  According to a third aspect of the present invention, the turbine is a partial feed turbine having a working fluid feed portion and a non-feed portion in the circumferential direction of the rotating portion.

  Thereby, the working fluid is fed from the feeding section, so that the stage nozzle and the stage blade in the feeding section are heated. Cooling can be effectively performed by injecting a high temperature vaporized material from a high temperature vaporized material injection part here.

  Moreover, in this invention of Claim 4, the high temperature vaporized material injection part has been arrange | positioned in the non-feeding part, It is characterized by the above-mentioned.

  As a result, for the combination group of stage nozzles and stage blades in the infeed section, the high temperature vaporizer injection section arranged in the non-infeed section with respect to the stage nozzle and stage rotor blades that have moved to the non-infeed section. Cooling can be performed effectively by injecting high-temperature vaporized material.

  Further, in the present invention described in claim 5, the high-temperature vaporized substance injecting section is provided in a non-feeding section near the feeding section on the downstream side in the rotation direction of the turbine rotating section.

  Thereby, immediately after the combination group of the stage nozzle and the stage rotor blade in the feeding part moves from the feeding part to the non-feeding part by the rotation of the turbine rotating part, the high-temperature vaporized substance is discharged from the high-temperature vaporized substance injection part. The combination group of the stage nozzle and the stage rotor blade can be effectively cooled by spraying.

  Further, in the present invention according to claim 6, the high temperature vaporized product injecting section has an arrangement configuration in which an injection direction is determined so as to inject high temperature vaporized material corresponding to the moving blade, the rotating shaft or the turbine disk. It is characterized by that.

  Thereby, it can cool effectively as a whole by injecting with respect to not only a moving blade but a rotating shaft and a turbine disk exposed to high temperature.

  Moreover, in this invention of Claim 7, the high temperature vaporized material in a high temperature vaporized material injection part is an ablation material, It is characterized by the above-mentioned.

  Thereby, even if it is a use condition that turbine inlet temperature exceeds a limit, it can cool effectively.

  Further, the present invention according to claim 8 is characterized in that the high-temperature vaporized substance in the high-temperature vaporized product injecting section is seawater.

  Thereby, even if it is seawater, if it is for cooling of what presupposes use for a short time, it can fully be used for cooling.

  According to the present invention, by injecting the high temperature vaporized material from the high temperature vaporized material injection unit to the turbine rotating unit, the turbine can be effectively operated in a limited space without using a cooling method such as film cooling or hollow cooling. A cooling structure in the turbine that can be cooled can be provided.

It is principal part expanded sectional explanatory drawing which shows an example of the turbine which comprises the cooling structure concerning this invention. It is a typical principal part explanatory drawing of 1st Embodiment of the cooling structure of the turbine concerning this invention. (A) Schematic principal part explanatory drawing of 2nd Embodiment of the cooling structure of the turbine concerning this invention, (b) When it sees from the inlet side in the central axis direction of the turbine rotation part in 2nd Embodiment, It is the figure which showed the sending-in part and the sending-in part typically. It is the figure which showed typically the non-feeding part and the feeding part when it sees from the entrance side in the center axis direction of the turbine rotation part in 3rd Embodiment of the cooling structure of the turbine concerning this invention. It is a typical principal part explanatory drawing of 4th Embodiment. (A) Arrangement of high-temperature vaporized substance injection section in the non-feed section and the feed section when viewed from the inlet side in the central axis direction of the turbine rotating section in the fourth embodiment of the turbine cooling structure according to the present invention Schematic diagram showing an example of the pattern, (b) a schematic diagram showing another example of the arrangement pattern of the high-temperature vaporized substance injection unit, (c) a schematic diagram showing another example of the arrangement pattern of the high-temperature vaporized substance injection unit. .

  Embodiments of a turbine cooling structure according to the present invention will be described below with reference to the accompanying drawings.

(First embodiment)
FIG. 1 schematically shows a first embodiment of a turbine cooling structure according to the present invention.
The turbine 1 here is a so-called axial turbine, which is supported by a supply port 4a of a working fluid supply pipe 4 fixed integrally with a stationary portion 3 outside the rotating shaft 2, and a working fluid (steam, combustion gas). ), The first stage moving blade 6b1 arranged immediately downstream of the first stage nozzle 5n1 and fixed to the rotating shaft 2 via the turbine disk 2d1, and the rotation of the first stage nozzle 5n1 and the first stage moving blade 6b1 The configuration includes a combination group of a plurality of stage nozzles 5n and stage rotor blades 6b supported by the rotary shaft 2 via a turbine disk 2d, which are sequentially arranged on the downstream side in the axial direction of the shaft 2.
Although the details will be described later, the turbine 1 is a partial feeding turbine having a working fluid feeding portion and a non-feeding portion in the circumferential direction of the rotating shaft 2.

  In the turbine 1, the working fluid that has flowed into the supply port 4 a through the working fluid supply pipe 4 fixedly supported on the stationary part 3 side flows into the first stage nozzle 5 n 1 and the first stage rotor blade 6 b 1 and performs expansion work. . Next, the working fluid flows into the downstream stage nozzle 5n and the stage rotor blade 6b, performs expansion work, and has a function of rotating the rotating shaft 2.

In the turbine 1 configured as described above, the turbine 1 is schematically shown in FIG. 2 in order to explain the present embodiment. In FIG. 2, the first stage nozzle 5n1 supported at the downstream end of the supply port 4a of the working fluid supply pipe 4 fixedly supported on the stationary part 3 side, the rotary shaft 2 as the turbine rotary part, and the rotary shaft 2 side are supported. The first stage rotor blade 6b1 is shown.
That is, FIG. 2 shows the turbine 1 as a schematic diagram in the working fluid feeding section.
Then, at a suitable position of the stationary part 3, the high-temperature vaporized material is vaporized by injecting the high-temperature vaporized material toward the first-stage moving blade 6b1 supported on the rotating shaft 2 side, thereby cooling the first-stage moving blade 6b1. A high temperature vaporized substance injection unit 10 is provided.

  The high-temperature vaporized substance injection unit 10 has an injection head 10 h for injecting a high-temperature vaporized substance mounted on the stationary part 3. Although the detailed configuration is not shown, the injection head 10h corresponds to the physical properties (viscosity) of the high-temperature vaporized material used, and the shape of the injection port so that it can be injected to the turbine rotating part (here, the first stage blade 6b1). The injection direction is set.

High-temperature vaporized material is a substance that vaporizes at a high temperature (assuming 800 ° C. or higher here), and is injected, applied to the turbine rotating part in a solid (granular material), solid-liquid two-phase flow, or liquid state, Or if it can spray, the composition is appropriate.
For example, an ablator can be used as the high-temperature vaporized material. The ablator is a fiber reinforced plastic heat-resistant material made by impregnating synthetic resin into carbon fiber or glass fiber, for example. It begins to decompose at temperatures above 300 ° C, and the reaction heat is generated from the base material when pyrolyzing. Take away. As a result, an injection film of high temperature vaporized material is formed by injection from the injection head 10h of the high temperature vaporized material injection unit 10 and the surface of the first stage rotor blade 6b1 of the turbine rotating unit is formed by injection, and this injection film undergoes thermal decomposition at high temperatures. The function is to take heat from the turbine rotating part and cool the turbine rotating part.

In the turbine cooling structure of the first embodiment as described above, the rotating shaft 2, the turbine disk 2d, and the rotor blade 6b are brought into direct contact with each other by feeding a working fluid, and the temperature thereof is increased.
Here, high temperature vaporized material (ablator) is ejected from the ejection head 10h of the high temperature vaporized material ejecting unit 10 mounted on the stationary part 3, thereby forming a spray film on the heated blade 6b. If the moving blade 6b exceeds 800 ° C., the spray film of the ablator on the moving blade 6b is thermally decomposed and vaporizes from the surface of the moving blade 6b to take heat away. In particular, the turbine rotating part including the moving blade 6b Can be cooled.

The turbine cooling structure according to the present invention can also be implemented by the following second embodiment. In the present embodiment, components that are substantially the same as those of the first embodiment described above are denoted by the same reference numerals and description thereof is omitted.
(Second Embodiment)
FIG. 3 a schematically shows a turbine 1 for implementing the turbine cooling structure in the second embodiment. In addition, since the structure of turbine 1 itself is the same as that of 1st Embodiment, detailed description is abbreviate | omitted.
Further, in the turbine 1 of the second embodiment, on the working fluid introduction side of the turbine rotating portion, the feeding portion 3a that is an area where the working fluid can be introduced, and the partition wall provided so as not to introduce the working fluid are provided. A feeding section 3b is provided (see FIG. 3b). The infeed portion 3a is set in the approximately 1/3 area on the working fluid introduction side of the turbine rotating portion, while the non-inlet portion 3b is set in the remaining approximately 2/3 area.
A plurality of high-temperature vaporized substance injection units 10 are provided over the entire surface of the non-feeding part 3b at appropriate intervals in the non-feeding part 3b on the working fluid introduction side of the turbine rotating part.

In the second embodiment as described above, the working fluid is fed from the area of the feeding section 3a, flows into the first stage nozzle 5n1 and the first stage blade 6b1, and then flows into the downstream stage nozzle 5n and the stage blade 6b. Thus, expansion work is performed, and the rotating shaft 2 of the turbine 1 rotates.
When the rotating shaft 2 of the turbine 1 rotates and the first stage nozzle 5n1 and the first stage rotor blade 6b1, and the downstream stage nozzle 5n and the stage rotor blade 6b are brought to the non-feeding portion 3b, a plurality of high temperature air High-temperature vaporized material is injected from the vapor injection unit 10 toward the first-stage nozzle 5n1 and the first-stage moving blade 6b1, and these surfaces are covered with the high-temperature vaporized material.
At this time, the first stage rotor blade 6b1 is exposed to the working fluid and is particularly heated. Therefore, when the high-temperature vaporized material is injected onto the surface of the first stage rotor blade 6b1, the high-temperature vaporized substance is vaporized, and the first stage rotor is moved by the endothermic reaction. The blade 6b1 can be cooled.
While the turbine 1 rotates in an area of approximately 2/3 that is the non-feeding portion 3b, the high-temperature vaporized material is uniformly injected from the high-temperature vaporized material injection unit 10 onto the moving blade 6b.

The turbine cooling structure according to the present invention can also be implemented by the following third embodiment. In the present embodiment, components that are substantially the same as those of the first embodiment described above are denoted by the same reference numerals and description thereof is omitted.
(Third embodiment)
FIG. 4 shows the working fluid introduction side of the turbine rotating part of the turbine 1 in the third embodiment. In such 3rd Embodiment, the high temperature vaporization injection | pouring part 10 is provided in the position immediately after completion | finish of partial feeding in the non-feeding part 3b. That is, the high temperature vaporized substance injection part 10 is provided in the non-feeding part 3b in the vicinity of the feeding part 3a on the downstream side in the rotation direction of the rotating part.

In the third embodiment as described above, when the turbine 1 rotates, the first stage nozzle 5n1 and the first stage nozzle 5n1 at the position where the working fluid is fed from the feeding part 3a to the non-feeding part 3b. The first stage rotor blade 6b1, and the downstream stage nozzle 5n and the stage rotor blade 6b are heated to the highest temperature by the working fluid.
Accordingly, the first-stage nozzle 5n1 and the first-stage nozzle immediately after the transition from the high-temperature vaporized material injection section 10 provided in the non-infeed section 3b in the vicinity of the infeed section 3a on the downstream side of the rotation section to the non-infeed section 3b. By injecting the moving blade 6b1 and the downstream stage nozzle 5n and the stage moving blade 6b, effective cooling of the first stage nozzle 5n1 and the first stage moving blade 6b1, and the downstream stage nozzle 5n and the stage moving blade 6b is achieved. I can expect.

The turbine cooling structure according to the present invention can also be implemented by the following fourth embodiment. In the present embodiment, components that are substantially the same as those of the first embodiment described above are denoted by the same reference numerals and description thereof is omitted.
(Fourth embodiment)
5 and 6 show a turbine cooling structure according to the fourth embodiment.
In the fourth embodiment, spray application is performed on the moving blade 6b, the rotary shaft 2 or the turbine disk 2d in accordance with the arrangement configuration of the high-temperature vaporized substance injection unit 10.
Here, a plurality of high-temperature vaporized substance injection sections 10 are provided at appropriate intervals in the non-infeed section 3b on the working fluid introduction side of the turbine rotating section, as shown in FIGS. 6a, 6b, and 6c. Thus, it can arrange | position with various arrangement | positioning patterns (injection direction).

First, in FIG. 6 a, the high-temperature vaporized material injection unit 10 injects the high-temperature vaporized material into the rotor blade 6 b attached to the turbine disk 2 d of the rotating shaft 2 in the rotating unit. In this way, the injection direction is set in the direction of the radius reaching the tip of the moving blade 6b with the rotary shaft 2 as the center.
Thereby, a high temperature vaporized material can be preferentially injected with respect to the moving blade 6b, and it is effective for cooling of the moving blade 6b.

In FIG. 6 b, the high-temperature vaporized substance injection unit 10 is arranged such that the high-temperature vaporized substance is injected with respect to the rotating shaft 2 in the injection direction of the high-temperature vaporized substance.
As a result, the high-temperature vaporized material is injected intensively with respect to the rotating shaft 2, and the rotating shaft 2 can be effectively cooled.

Furthermore, in FIG. 6c, the high temperature vaporized substance injection | pouring part 10 is distributed and arrange | positioned so that the injection direction of a high temperature vaporized substance may reach | attain uniformly with respect to the moving blade 6b, the rotating shaft 2, or the turbine disk 2d. .
Thereby, the high-temperature vaporized material is uniformly injected to the rotor blade 6b, the rotating shaft 2 or the turbine disk 2d, which is the rotating part, and the entire rotating part can be effectively cooled.

The turbine cooling structure according to the present invention has been described with reference to the accompanying drawings by giving the first to fourth embodiments.
Of course, the present invention is not limited to these first to fourth embodiments. For example, in the first to fourth embodiments, among the partial-feed turbines, the feed-in part 3a is in an approximately 1/3 area on the working fluid introduction side of the turbine rotating part, and the non-feed-in part 3b is Although the configuration in which the remaining approximately 2/3 of the area is set has been described, the arrangement pattern of the feeding portion and the non-feeding portion may be changed.
By changing the arrangement pattern of the feeding part 3a and the non-feeding part 3b, the way of arranging the high-temperature vaporized substance injection part 10 also changes and the cooling efficiency also changes.

Moreover, although the high-temperature vaporized material of the high-temperature vaporized material injection part 10 was also demonstrated using the ablation material, seawater can also be used when the necessary minimum cooling degree is sufficient.
Seawater is particularly readily available when the turbine 1 is used in an underwater vehicle, and manufacturing costs can be reduced.

  The present invention is highly versatile for a turbine of a geothermal power generation device used in the ground, in addition to underwater, for example, if it is a turbine premised on use in an environment where air cooling is impossible.

DESCRIPTION OF SYMBOLS 1 Turbine 2 Rotating shaft 2d, 2d1 Turbine disk 3 Stationary part 3a Inlet part 3b Non-inlet part 4 Working fluid supply pipe 4a Supply port 5n1 First stage nozzle 6b1 First stage moving blade 10 High temperature vaporized substance injection part

Claims (8)

A cooling structure in a turbine that cools a turbine rotating part with respect to a turbine operated by a working fluid,
A cooling structure in a turbine, comprising: a high-temperature vaporized material injection unit that injects high-temperature vaporized material into the turbine rotating unit to vaporize the high-temperature vaporized material and cool the turbine rotating unit. The turbine rotating unit includes a rotating shaft, a turbine disk, and a moving blade.
The cooling structure in a turbine according to claim 1, wherein   2. The cooling structure for a turbine according to claim 1, wherein the turbine is a partial feed turbine having a working fluid feeding portion and a non-feeding portion in a circumferential direction of the turbine rotating portion.   The cooling structure for a turbine according to claim 3, wherein the high-temperature vaporized substance injection part is disposed in the non-feed-in part.   The cooling structure for a turbine according to claim 4, wherein the high-temperature vaporized substance injection section is provided in the non-feed section in the vicinity of the feed section on the downstream side in the rotation direction of the turbine rotating section.   The high-temperature vaporized substance injecting section has an arrangement configuration in which an injection direction is determined so as to inject the high-temperature vaporized substance corresponding to the moving blade, the rotating shaft, or the turbine disk. The cooling structure in the turbine according to claim 2.   The cooling structure for a turbine according to any one of claims 1 to 6, wherein the high-temperature vaporized substance in the high-temperature vaporized substance injection section is an ablation material. The cooling structure in a turbine according to any one of claims 1 to 6, wherein the high-temperature vaporized substance in the high-temperature vaporized substance injection unit is seawater.

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