JPH0316569B2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION (Field of Industrial Application) The present invention relates to a liner for a gas turbine combustor, and more particularly to a liner wall structure with high heat resistance.

(Prior Art) In a gas turbine combustor, as shown in FIG. 2, the metallic liner 1 is exposed to the high temperature combustion gas G in the combustion chamber 2 and becomes high temperature. This cooling air A is introduced into the combustion chamber 2 through an opening 3 provided in the liner 1. The air introduced into the combustion chamber 2 is used for secondary combustion.

However, in order to improve the performance of the gas turbine, it is necessary to increase the combustion temperature, but if the combustion temperature is increased, the liner 1 will not be able to withstand the high temperature and will be thermally destroyed.

In order to improve the heat resistance of the liner 1, it is also known to line the liner 1 with dense ceramics 4 for heat shielding.

(Problems to be Solved by the Invention) However, since the conventionally known lined ceramic 4 itself becomes high temperature, the liner 1 receives radiation heat and heat conduction from this ceramic 4 and becomes high temperature, so that the improvement in heat resistance cannot be achieved. It has not yet become sufficient.

(Means for Solving the Problems) The present invention is characterized by providing an opening of a predetermined size in a metal liner, and lining the metal liner with porous ceramics having a predetermined amount of gas passing through. There is a place where it becomes.

(Example) Hereinafter, an example of the present invention will be described with reference to FIG.

A porous ceramic 12 is lined inside a metal liner 11 with a thin cushioning material 13 interposed therebetween.

The cushioning material 13 is made of a heat-resistant ceramic fiber material, which absorbs the difference in thermal expansion that occurs between the liner 11 and the porous ceramics 12, and facilitates the lining work of the porous ceramics 12, which has little elastic deformation. It is something.

The liner 11 is provided with a predetermined opening 14, and the air flowing through the cooling air passage 15 is introduced into the combustion chamber 16 through the porous ceramics 12 for secondary combustion.

For this reason, the porous ceramic 12 having pores large enough to allow a predetermined amount of gas to pass through is used.

High-temperature combustion gas G generated from the fuel nozzle and swirler 17 flows in the combustion chamber 16 as a swirling flow. Therefore, the porous ceramics 12 is superheated by the combustion gas.

On the other hand, cooling air enters the combustion chamber 16 from the cooling air passage 15 through the opening 14 and the porous ceramics 12. When the air passes through the porous ceramics 12, the porous ceramics 12
to cool down. For this reason, porous ceramics 1
This prevents the liner 2 from reaching a high temperature, which in turn prevents the liner 11 from reaching a high temperature.

Although the above explanation describes the liner of a gas turbine combustor, the present invention is applicable to a combustor that requires air for secondary combustion or a combustion system that does not cause any problem even if cooling air is introduced into the combustion chamber. It goes without saying that it can be applied to the inner walls of vessels.

It also includes changing the amount of pores in the porous ceramic in the flow direction of the high-temperature combustion gas.

(Effects of the Invention) It is possible to maintain a uniform temperature over the entire surface of the liner, raise the combustion temperature, and obtain a high-performance gas turbine combustor.

By using porous ceramics,
Since the temperature of the ceramic itself is lowered, the liner is not overheated due to heat radiation or conduction from the ceramic itself.

Since ceramics have weak outward radiation and strong inward radiation, a uniform temperature field is obtained within the combustion chamber, and combustion occurs due to radiant heat, preventing incomplete combustion.

The cushioning material absorbs the difference in thermal expansion and shields vibrations, so there is no breakage or damage to the porous ceramics, improving durability and simplifying manufacturing work.

[Brief explanation of the drawing]

FIG. 1 is a sectional view of a combustor showing an embodiment of the present invention, and FIG. 2 is a schematic sectional view of a conventionally known gas turbine combustor. 11: Liner, 12: Porous ceramics, 13: Cushioning material, 14: Opening.

Claims (1)

[Claims] 1. A liner for a gas turbine combustor, characterized in that a metal liner is provided with an opening of a predetermined size, and the metal liner is lined with porous ceramics having a predetermined amount of gas passing through.