JPH07119489A - Cooling device for turbine stationary blade - Google Patents

Abstract

PURPOSE:To cool a stationary vane without feeding cooling air in the stationary vane by a method wherein the heat absorbing part of a heat pipe is arranged to each turbine stationary blade and the radiation part of the heat pipe is arranged to the inner upper half part of a bypass air duct. CONSTITUTION:Metallic fluid, such as potassium and sodium, is used as internal fluid of a heat pipe 20. The heating medium transfer pipe 22 of the heat pipe 20 is connected to one of heat absorbing parts 21 arranged in an annular manner according to arrangement of a stationary vane 12 and one of radiation parts 23 arranged in a semicircular shape. A lower half heat absorbing part 21 is connected to a right heat-exchange part R and left heat-exchange part L and the upper half heat absorbing part 21 is connected to an upper jeer heat- exchange part T. When the stationary vane 12 is exposed to high temperature atmosphere and temperature is increased, the heat thereof is transmitted to the heat absorbing part 21. The stationary vane 12 is cooled by the steam latent heat of internal fluid, internal fluid is raised in a heating medium transfer pipe 22 and guided to radiation part 23 and cooled by air in a bypass air flow passage 14 and a latent heat content is discharged. As noted above, cooling is effected without feeding cooling air in the stationary blade.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a cooling device for turbine vanes, and more particularly to a technique for cooling turbine vanes using a heat pipe.

[0002]

2. Description of the Related Art FIG. 3 shows a structural example of a gas turbine engine (turbo fan engine) used in an aircraft. In the figure, reference numeral 1 is an air intake port, 2 is a low pressure compressor,
3 is a fan air exhaust duct, 4 is a high pressure compressor, 5 is a combustion chamber, 6 is a high pressure turbine, 6a is a turbine shaft, 7 is a low pressure turbine, 8 is an exhaust duct, 9 is a disk, 10 is a moving blade,
11 is a casing, 12 is a vane (turbine vane), 13
Is a bypass duct, and 14 is a bypass air flow path.

Conventionally, as a method for cooling the stationary blades 12 in the low pressure compressor 2, the high pressure compressor 4, the high pressure turbine 6 and the low pressure turbine 7, for example, a cooling flow path such as a meandering state is provided inside the stationary blades 12. There have been considered a technique for forming and forming the cooling air by sending the extracted bleeding air, and a technique for ejecting the cooling air to the front edge portion of the stationary blade 12 to accelerate cooling in the vicinity thereof.

[0004]

However, in the technique of forming the cooling flow passages inside the stationary blade 12, if the number of cooling flow passages is increased so as to improve the contactability with the cooling air, the stationary blades will be formed. If the cooling air is jetted from the stationary vanes 12, unnecessary cooling air will be sent to the high-pressure turbine 6 and the like, thereby lowering the thermal efficiency of the gas turbine. It will be one of the factors that cause it.

The present invention has been made in view of these problems, and an object thereof is to effectively cool the vane without sending cooling air into the vane.

[0006]

When cooling a turbine vane by heat transfer from a heat pipe, a heat absorbing portion of the heat pipe is arranged in each turbine vane, and heat is transferred to the upper half of the bypass air duct. The cooling device for the turbine vane has a structure in which the heat radiation part of the pipe is arranged.

[0007]

When the turbine vane becomes hot, heat is transferred from the turbine vane to the heat absorbing portion of the heat pipe by heat conduction, and the liquid inside the heat pipe is vaporized and guided upward. The vapor passes through the inside of the heat pipe and rises to the heat dissipation portion. The heat radiating portion is cooled by heat exchange with the bypass air in the bypass air duct, and the vapor is condensed into a liquid. This condensate circulates back to the heat absorbing section by the wick in the heat pipe based on gravity.
When radiating and condensing these internal liquids, if the heat radiating portion is arranged in the upper half of the bypass air duct, the vapor rises and one condensate goes down and one condensate goes down one pass. The resistance during circulation is reduced.

[0008]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT An embodiment of a cooling device for a turbine vane according to the present invention will be described below with reference to FIGS. 1 and 2, reference numeral 20 is a heat pipe,
Reference numeral 21 is a heat absorbing portion, 22 is a heat medium transfer pipe, 23 is a heat radiating portion, 24
Is a radiating fin, A, B, C, D, E and F are bent portions, T is an upper heat exchange portion, R is a right heat exchange portion, and L is a left heat exchange portion.

For the heat pipe 20, an internal fluid is selected in consideration of the ambient temperature range of the stationary blade 12, and for example, a metal fluid such as potassium or sodium having a working temperature range of 500 to 1200 ° C. is applied. When the internal fluid is potassium or sodium, stainless steel, nickel, Inconel, or the like is applied as the material (pipe material) of the heat medium transfer pipe 22, and as the wick material inserted into the heat medium transfer pipe 22, Ceramic fibers or metal fibers are applied.

The heat absorbing portion 21 is integrally embedded in each of the stationary vanes 12, and the heat exchanging portions T, which are arranged in the upper half of the bypass air passage 14 by the heat medium transfer pipe 22, are provided.
It is connected to R and L.

As shown in FIG. 1, the heat transfer medium transfer pipe 22 includes one of the heat absorbing parts 21 arranged in a ring shape and the heat radiating part 23 arranged in a semicircle according to the arrangement of the respective vanes 12. Of the lower half of the heat absorbing part 21 is connected to the right side heat exchanging part R and the left side heat exchanging part L, and the upper half of the heat absorbing part 21 is connected to the upper side. It is connected to the heat exchange section T. That is, for the lower half heat absorbing part 21,
As shown in FIG. 2, after the heat transfer medium transfer pipe 22 is drawn inward from the stationary blade 12 in the radial direction, it is bent in the circumferential direction at the bent portion A and guided along the circumferential direction, and is bent at the bent portion B in the radius direction. After being bent outward, it penetrates the inside of the stationary blade 12 in the vicinity thereof and is pulled out to the outside of the stationary blade 12, then is bent in the circumferential direction at the bent portion C and guided along the circumferential direction, By being bent at the bent portion D, it is connected to the heat dissipation portion 23. Then, as shown in FIG. 1, the upper half heat absorbing portion 21 is pulled out from the vane 12 in the radial outward direction and is bent twice at, for example, the bending portions E and F, and then the upper heat exchange is performed. It is connected to the heat dissipation part 23 in the range of the part T.

In the turbine stator blade cooling device thus constructed, both compressors 2, 4 and both turbines 6,
When 7 becomes an operating state, the stationary blade 12 is exposed to a high temperature atmosphere, and the temperature of the stationary blade 12 rises.

At this time, the heat of the stationary blades 12 is transferred to the heat absorbing portion 21 of the heat pipe 20 by heat conduction, vaporization of the liquid inside the heat pipe 20 occurs, and the latent heat (vaporization heat) is taken away, so that the heat is removed. Cool the wings 12.

In the heat absorbing portion 21 of the heat pipe 20,
The internal fluid that has been vaporized by absorbing heat sequentially rises in the heat medium transfer pipe 22 and is guided to the heat radiating portion 23, as shown by the solid arrow in FIG.

The heat radiating section 23 is cooled by heat exchange with the bypass air sent to the bypass air flow path 14 in the bypass duct 13, and the vapor in the heat radiating section 23 is condensed and liquefied to generate heat of latent heat. discharge.

The condensate in the heat radiating portion 23 flows down to the heat absorbing portion 21 by virtue of the action of gravity via the wick in the heat medium transfer pipe 22, as indicated by the dashed arrow in FIG.
It vaporizes again and rises along the heat medium transfer pipe 22.

When these vapors rise and liquids flow down, as shown in FIG. 2, the lower half vane 12 is connected to the right side heat exchange section R or the left side heat exchange section L, and its heat medium is connected. By the transfer pipe 22 being bent at the bent portions A, B, C, D and passing through one of the upstream and downstream transmission paths,
Smooth circulation is achieved. In the upper half vane 12, the heat medium transfer pipe 22 disposed outside the heat absorbing part 21 by the heat medium transfer pipe 22 is bent at two bent portions E and F as necessary. As a result, the vapor and the liquid pass through one of the upstream and one of the downstream transmission paths, whereby smooth circulation is performed.

[Other Embodiments] In the present invention, the following techniques can be adopted instead of the embodiments. a) Heat for cooling the other parts of the bypass air flow passage 14 in order to give flow passage resistances commensurate with the upper heat exchange portion T, the right heat exchange portion R and the left heat exchange portion L to the lower half. Place replacement parts and dummy members. b) A plurality of stationary blades 12 are connected in parallel to the heat absorbing portion 21, the heat medium transfer pipe 22 or the heat radiating portion 23 of the heat pipe 20 so that the internal fluid is shared.

[0019]

The cooling device for a turbine vane according to the present invention has the following effects. (1) Since a heat pipe is arranged between the turbine vane and the inside of the bypass duct to cool the turbine vane, heat is not exchanged with the heat pipe without sending cooling air into the vane. The heat exchange based on conduction can be performed to effectively cool the vanes. (2) By disposing the heat radiating portion of the heat pipe in the upper half of the bypass air duct, the resistance of the circulation path is reduced by making the vapor ascending path upward and the condensate descending path downward. The heat exchange efficiency can be improved.

[Brief description of drawings]

FIG. 1 is a cross-sectional view showing an embodiment of a cooling device for a turbine vane according to the present invention.

FIG. 2 is an enlarged view showing the relationship between the stationary blade and the heat pipe of FIG.

FIG. 3 is a front sectional view showing a structural example of a gas turbine engine.

[Explanation of symbols]

 1 Air Intake 2 Low Pressure Compressor 3 Fan Air Discharge Duct 4 High Pressure Compressor 5 Combustion Chamber 6 High Pressure Turbine 7 Low Pressure Turbine 8 Exhaust Duct 11 Casing 12 Static Blade (Turbine Static Blade) 13 Bypass Duct 14 Bypass Air Flow Path 20 Heat Pipe 21 heat absorption part 22 heat medium transfer pipe 23 heat dissipation part 24 heat dissipation fins A, B, C, D, E, F bent part T upper heat exchange part R right heat exchange part L left heat exchange part

Claims (1)

[Claims] 1. A turbine vane is cooled by heat transfer from a heat pipe, wherein each turbine vane is provided with a heat absorbing portion of the heat pipe, and a heat pipe of the heat pipe is provided in an upper half of the bypass air duct. A cooling device for a turbine vane, characterized in that a heat radiating portion is provided.