JPH07269865A - Flame holding device of combustion device - Google Patents

Abstract

PURPOSE:To provide a flame holding device for a gas turbine combustion device having a high thermal reliability. CONSTITUTION:A flame holding device 1 for a combustion device is comprised of a flame holding surface 2 and a supporting part 3. A cooling medium feeding flow passage 5 is inserted into an internal cooling space 4 enclosed by the supporting part 3. In addition, the supporting part 3 near a part where the cooling medium feeding flow passage 5 is connected is provided with a plurality of cooling medium flowing-out ports 6. The flame holding device 1 for the combustion device is cooled from outside with air 10 flowing along an outer shell and concurrently it is cooled with fuel 11 flowing in the internal cooling space 4 of the flame holding device 4 of the combustion device. With such an arrangement as above, it is possible to provide a flame holding device of a gas turbine combustion device having a high thermal reliability in operation.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flame stabilizer for a combustor which retains flames by utilizing a recirculation flow formed in the wake of the flame retaining surface, and more particularly to a gas turbine combustor for high temperature or high load combustion. A suitable flame stabilizer.

[0002]

2. Description of the Related Art Conventionally, in a gas turbine combustor,
A flame stabilizer is installed as one measure for flame stabilization, that is, stabilization of the flame, and the flame is maintained by the high-temperature gas recirculation flow formed in the subsequent flow (Book "Basics and Applications of Combustion"). Pp. 172-173). In that case, the flame stabilizer having a high temperature is cooled by a fluid such as air flowing outside the flame stabilizer and set to a temperature lower than the heat resistant temperature.

[0003]

However, in recent years, as the combustion gas temperature is raised to improve the power generation efficiency, the environment in which the flame stabilizer is used has become more severe, and the flame stabilizer has even higher heat resistance. And it is necessary to improve thermal reliability.

An object of the present invention is to provide a flame stabilizer for a gas turbine combustor having high thermal reliability.

[0005]

According to the flame stabilizer of the present invention, a cavity is provided inside the flame stabilizer, and a cooling medium introducing passage for introducing a cooling medium into the cavity and a cooling medium in the cavity are provided. And a cooling medium outflow passage for allowing the air to flow out of the cavity.

[0006]

As a result of the above structure, the temperature rise of the flame stabilizer can be suppressed by the synergistic effect of the cooling effect by the fluid flowing inside the flame stabilizer in addition to the cooling effect by the fluid flowing outside the conventional flame stabilizer.

[0007]

Embodiments of the present invention will be described below by taking a flame stabilizer for a high temperature gas turbine combustor for premixed combustion as an example.

FIG. 1 is an axial sectional view of a flame stabilizer for a gas turbine combustor showing an embodiment of the present invention. The flame holder 1 for a combustor has an outer shell formed by a circular flat flame holding surface 2 and a supporting portion 3 composed of an inclined portion and a straight portion, and a cooling medium is provided in an internal cooling space 4 surrounded by the supporting portion 3. The introduction flow path 5 is inserted. Further, a plurality of cooling medium outlets 6 are provided in the supporting portion 3 near the joint of the cooling medium introducing flow paths 5. The outer shell 7 of the combustor is the flame stabilizer 1 for the combustor described above.
The ignition plug 8 is provided in the vicinity of the flame holding surface 2 of the combustor outer shell 7 while being held so as to surround the flame holding surface 2 of the combustor outer shell 7 and The facing space is formed as a combustion chamber 9.

Next, the operation of this embodiment will be described.

In FIG. 1, the air 10 flows into the combustion chamber 9 along the inside of the combustor outer shell 7 along the outer shell of the combustor flame stabilizer 1, and the fuel 11 is supplied to the combustor through the cooling medium introducing passage 5. After being introduced into the internal cooling space 4 of the flame stabilizer 1, it is mixed with the air 10 via the cooling medium outlet 6. A mixed gas 12 of air 10 and fuel 11 flows into the combustion chamber 9 and forms a circulation flow 13 downstream of the flame stabilizing surface 2. Circulating flow 1 by spark plug 8
3 is ignited, flame 14 is formed, and combustion gas 15 is generated. After ignition, flame holding surface 2 is flame 14 and high temperature combustion gas 1
It is heated by the radiant heat from 5, and the temperature rises. The flame holding surface 2 is the air 1 flowing along the outer shell of the flame holder 1 for the combustor.
Since it is cooled from the outside by 0 and is cooled by the fuel 11 flowing in the internal cooling space 4 of the flame stabilizer 1 for the combustor, its temperature rise is suppressed.

According to this embodiment, since the flame stabilizer for the combustor is cooled by the fuel having the low temperature, the temperature rise can be effectively suppressed.

FIG. 2 is an axial sectional view of a flame stabilizer for a gas turbine combustor according to another embodiment of the present invention. Figure 1
Part of the difference from the above will be explained.

2 is different from FIG. 1 in that a vane 16 is provided at an end of a cooling medium introducing passage 5 inserted into an internal cooling space 4 of the flame stabilizer 1 for the combustor. In the present embodiment, the vane 16 is angled from the end of the cooling medium introduction flow path 5 on a straight line connecting the corner 17 where the flame holding surface 2 is joined to the support portion 3 and the end of the cooling medium introduction flow path 5. It is characterized in that it is provided up to a position not in contact with the portion 17. This vane 16
As a result, the fuel 11 flows in the internal cooling space 4 along the inside of the corner portion 17, so that the thermal stress becomes large.
7 can be cooled more reliably.

According to this embodiment, the flame stabilizer for the combustor can be cooled more uniformly.

[0015]

According to the present invention, a flame stabilizer for a gas turbine combustor having high thermal reliability can be provided.

[Brief description of drawings]

FIG. 1 is an axial cross-sectional view of a flame stabilizer for a gas turbine combustor showing an embodiment of the present invention.

FIG. 2 is an axial sectional view of a flame stabilizer for a gas turbine combustor according to another embodiment of the present invention.

[Explanation of symbols]

DESCRIPTION OF SYMBOLS 1 ... Flame stabilizer for combustor, 2 ... Flame holding surface, 3 ... Support part, 4 ... Internal cooling space, 5 ... Cooling medium introduction flow path, 6 ... Cooling medium outlet, 7 ... Combustor outer shell, 8 ... Ignition Stopper, 9 ... Combustion chamber, 10 ...
Air, 11 ... Fuel, 12 ... Mixed gas, 13 ... Circulating flow, 1
4 ... Flame, 15 ... Combustion gas, 16 ... Vane, 17 ... Corner.

Claims (4)

[Claims] 1. A flame stabilizer for a combustor, comprising: a flame holding surface that forms a combustion gas recirculation region and is heated by the heat of the combustion gas; and a support member that forms and supports the flame holding surface.
A cooling medium introduction flow path for hollowing the inside of the flame stabilizer and for introducing a cooling medium into the cavity, and a cooling medium outflow for causing the cooling medium in the cavity to flow out of the cavity. A flame stabilizer for a combustor, characterized by having a passage. 2. A flame stabilizer for a combustor according to claim 1, wherein
A combustor characterized in that one end of the cooling medium introducing passage is formed so as to project into the cavity, and the one end is provided at a position where the cooling medium ejected into the cavity directly injects onto the flame holding surface. Flame stabilizer. 3. A flame stabilizer for a combustor according to claim 1,
A flame stabilizer for a combustor, wherein fuel, air, or steam is used as the cooling medium. 4. A flame stabilizer for a combustor according to claim 2, wherein:
A flame stabilizer for a combustor, wherein a vane for changing a streamline of the cooling medium flowing in the cavity is provided at an end portion of one end of the cooling medium introduction flow channel protruding into the cavity.