JPH06173706A - Shroud housing structure for gas-turbine engine - Google Patents

Abstract

PURPOSE:To provide a shroud housing structure for a gas-turbine engine which can suppress reduction of efficiency of a turbine unit by keeping circularity of shroud ring as precisely as possible and forming an adequate space between the shroud ring and the blade tip of moving blade. CONSTITUTION:In a shroud housing structure for a gas-turbine engine provided with a shroud ring 10 positioned behind the combustion chamber of a gas-turbine engine and turbine stationary blades 6b, 7b fixed to the shroud ring faced to a turbine moving blades 6a, 7a rotated by a combustion gas exhausted from the combustion chamber. Heat pipes 11 are attached to the shroud ring 10 along circumferential direction, in the form of ring, to which the blade tips of turbine moving blades 6a, 7a are faced.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a shroud housing structure located rearward of a combustion chamber of a gas turbine engine.

[0002]

2. Description of the Related Art FIG. 3 shows an example of a conventionally used gas turbine engine. In this gas turbine engine, inflow air taken in from the air intake 1 is first compressed by the low pressure compressor 2. Then, a part of the compressed air sent from the low-pressure compressor 2 passes through the fan air exhaust duct 3 and is directly injected outside the engine as a bypass thrust.

On the other hand, the compressed air sent from the low-pressure compressor 2 is further compressed to a high pressure by the high-pressure compressor 4, and then sent to the combustion chamber 5 where it is mixed with the supplied fuel, gasified and burned. The exhaust gas discharged from the combustion chamber 5 rotates the compressor turbine 6 and the fan turbine 7, and is injected as core thrust by the exhaust duct 8.

The low-pressure compressor 2 comprises a fan rotor blade 2a and a fan stator blade 2b. The fan rotor blade 2a is connected to the fan turbine 7 via a fan turbine shaft 9. The high-pressure compressor 4 is composed of a fan rotor blade 4a and a fan stator blade 4b, the fan rotor blade 4a is connected to the compressor turbine 6 via a compressor turbine shaft, and the fan stator blade 4b is a shroud ring. It is fixed at 10.

The compressor turbine 6 comprises a turbine moving blade 6a and a turbine stationary blade 6b, and the fan turbine 7 comprises a turbine moving blade 7a and a turbine stationary blade 7b.
The turbine vanes 6b and 7b are the shroud ring 10
It is fixed to.

[0006]

By the way, although the compressor turbine 6 and the fan turbine 7 of the conventional gas turbine engine become high in temperature, the turbine vanes 6b and 7b are fixed to the shroud ring of this portion, which is complicated. Since the shape is such that the heat conduction becomes non-uniform, the non-uniform temperature distribution occurs in the shroud ring, and the shroud ring, which should be a perfect circle, undulates in the circumferential direction as shown in FIG. A phenomenon such as deformation occurs. Therefore, in order to prevent the contact between the shroud ring and the blade tip of the rotor blade,
It is necessary to provide an excessive gap e, and there is a problem that the efficiency of the turbine section is reduced due to the leakage of combustion gas from this gap.

The present invention has been made in view of the above circumstances, and it is possible to maintain the roundness of the shroud ring as much as possible, and to form an appropriate gap between the shroud ring and the blade tip of the moving blade. Accordingly, it is an object of the present invention to provide a shroud housing structure for a gas turbine engine that can suppress a decrease in efficiency of the turbine section.

[0008]

A gas turbine engine shroud housing structure according to the present invention is rotated by a shroud ring located at least rearward of a combustion chamber of a gas turbine engine and combustion gas discharged from the combustion chamber. In a shroud housing structure of a gas turbine engine, which comprises a turbine stationary blade fixed to the shroud ring facing a turbine moving blade to be made,
A heat pipe is attached in a ring shape along the outer peripheral surface of the shroud ring where the blade tips of the turbine rotor blades face each other.

[0009]

According to the shroud housing structure of the gas turbine engine of the present invention, since the ring-shaped heat pipe is mounted along the circumferential direction of the outer peripheral surface of the shroud ring, the combustion gas discharged from the combustion chamber causes Even if the shroud ring has a non-uniform temperature distribution, heat conduction occurs via the heat pipe, and the non-uniform temperature distribution is flattened. Therefore, it is possible to prevent the wavy phenomenon that occurs in the shroud ring due to the non-uniform temperature distribution. As a result, the shroud ring can be held in a perfect circular state, so that an appropriate gap can be formed between the shroud ring and the blade tip of the moving blade, and the efficiency of the turbine part is reduced. Can be suppressed to a low level.

[0010]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A gas turbine engine shroud housing structure according to an embodiment of the present invention will be described below with reference to the drawings.

As shown in FIG. 2, the compressor turbine 6 and the fan turbine 7 of this embodiment have a plurality of turbine rotor blades 6a, 7a provided at intervals along the circumferential direction and the turbine rotor blades 6a, 7a. A shroud ring 10 provided so as to surround the blades 6a, 7a from the periphery, and a shroud ring 10 mounted on the inner peripheral surface of the shroud ring 10 so as to face the turbine rotor blades 6a, 7a and spaced apart in the circumferential direction. It is provided with a plurality of turbine vanes 6b and 7b provided.
The shroud ring 10 is formed integrally with the portion surrounding the combustion chamber 5 and the high pressure compressor 4.

Here, a heat pipe 11 is attached in a ring shape along the circumferential direction to the outer peripheral surface of the shroud ring 10 where the blade tips of the turbine rotor blades 6a and 7a face each other. The heat pipe 11 has a tubular container filled with a working fluid such as metallic sodium and a wick for circulating the working fluid therein.
When heat is applied from the outside to the evaporation section of No. 1, the working fluid takes heat and evaporates, and the vapor flows at high speed toward the condensation section with low pressure, and the vapor reaching the condensation section releases latent heat of condensation. By liquefying it, a large amount of heat can be carried from the high temperature side to the low temperature side with a small temperature difference.

Next, the function and effect of the shroud housing structure of this embodiment will be described. The compressor turbine 6 and the fan turbine 7 are exposed to the combustion gas discharged from the combustion chamber 5 to raise the temperature. These shroud rings 1
At 0, the turbine vanes 6a and 7a are provided at intervals along the circumferential direction and have a complicated non-uniform shape in the circumferential direction, so that a non-uniform temperature distribution occurs in the circumferential direction and Due to the difference in thermal expansion of the shroud ring 10, the shroud ring 10 tries to wave in the circumferential direction.

However, the shroud ring 10
Since the heat pipe 11 is attached to the outer peripheral surface of the, the heat is transferred from the high temperature portion to the heat pipe 11 to eliminate the non-uniform temperature distribution, and the temperature of the shroud ring 10 becomes uniform. . Therefore, it is possible to suppress the waviness phenomenon of the shroud ring 10 that occurs when an uneven temperature distribution is generated, it is possible to maintain a high roundness, and the blade tips of the turbine rotor blades 6a and 7a are It is not necessary to have an excessive gap with the shroud ring 10, and the gap can be made appropriate. As a result, it is possible to suppress a decrease in the efficiency of the turbine unit due to gas leakage from the gap.

[0015]

As described above, according to the shroud housing structure of the gas turbine engine of the present invention, the heat pipe is attached in a ring shape along the circumferential direction to the shroud ring where the blade tips of the turbine rotor blades face each other. As a result, the uneven temperature distribution that occurs in the shroud ring is eliminated, the roundness of the shroud ring can be maintained as much as possible, and a proper gap is formed between the shroud ring and the blade tip of the blade. Therefore, it is possible to suppress deterioration of the efficiency of the turbine unit.

[Brief description of drawings]

FIG. 1 is a cross-sectional view showing a shroud housing structure according to an embodiment of the present invention.

FIG. 2 is a sectional view taken along the line EE in FIG.

FIG. 3 is a schematic diagram showing an overall configuration of a conventional gas turbine engine.

FIG. 4 is a diagram showing a drawback of a conventional shroud housing structure.

[Explanation of symbols]

 1 Air Intake 4 High Pressure Compressor 5 Combustion Chamber 6 Compressor Turbine 6a Turbine Blade 6b Turbine Stator 7 Fan Turbine 7a Turbine Blade 7b Turbine Stator 10 Shroud Ring 11 Heat Pipe

Claims (1)

[Claims] 1. A turbine fixed to the shroud ring facing a shroud ring located rearward of a combustion chamber of a gas turbine engine and a turbine rotor blade rotated by combustion gas discharged from the combustion chamber. In a shroud housing structure of a gas turbine engine including stationary vanes, a heat pipe is attached in a ring shape along a circumferential direction to the shroud ring where the blade ends of the turbine rotor blade face each other. Engine shroud housing structure.