JPH074661A - Gas turbine combustor - Google Patents

Gas turbine combustor

Info

Publication number
JPH074661A
JPH074661A JP14885893A JP14885893A JPH074661A JP H074661 A JPH074661 A JP H074661A JP 14885893 A JP14885893 A JP 14885893A JP 14885893 A JP14885893 A JP 14885893A JP H074661 A JPH074661 A JP H074661A
Authority
JP
Japan
Prior art keywords
flame
combustion
premixer
pilot burner
flame stabilizer
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
JP14885893A
Other languages
Japanese (ja)
Inventor
Shinichi Inage
Toshiyuki Tanaka
利幸 田中
真一 稲毛
Original Assignee
Hitachi Ltd
株式会社日立製作所
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hitachi Ltd, 株式会社日立製作所 filed Critical Hitachi Ltd
Priority to JP14885893A priority Critical patent/JPH074661A/en
Publication of JPH074661A publication Critical patent/JPH074661A/en
Pending legal-status Critical Current

Links

Abstract

PURPOSE:To provide a flame keeping device in which premixing combustion gas is likely to be fired, and which stably keeps a flame upon high load combustion, and further which is preferable for avoiding burning of a combustor. CONSTITUTION:Fuel gas 101 fed from a pilot burner fuel supply pipe 17 comes in contact with pilot burner air 101 at a pilot burner outlet 15 and is diffused and combusted there to form a diffusion flame 106. In contrast, a premixer 11 is constructed with a space around a pilot burner between the pilot burner and a cylindrical wall located outside the former. In the premixer 11, a premixing combustion fuel 18 and part 103 of air 102 fed from a compressor are mixed. The mixed air is fired with high temperature already combusted gas existent behind a flame keeping device 12 provided in the vicinity of the outlet of the premixer 11 to form a premixed flame.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine combustor having a premixer, and more particularly to a flame stabilizer suitable for stabilizing ignition at the start of premix combustion and flame holding at high load combustion. And a gas turbine combustor having a premixer with.

[0002]

2. Description of the Related Art Conventionally, diffusion combustion in which a fuel and an oxidizer are injected from different nozzles and brought into contact with each other in the combustor has been mainly adopted as a combustion method of a practical gas turbine combustor. Diffusion combustion is a safe combustion method because the combustion is rate-controlled by the diffusion of fuel and oxidant and the flame has no propagating property.

Recently, in response to high-load combustion and stricter regulations on air pollutants, premixed combustion has been adopted in which a mixed fuel gas in which fuel and air are mixed in advance is sent to a combustion chamber for combustion. In the diffusion combustion, the concentration of fuel is unevenly generated, and a large amount of NOx is generated where the combustion temperature locally rises.
In the premixed combustion, the fuel and the air are uniformly mixed in advance. Therefore, it is possible to realize the ultra-low NOx combustion in which the NOx is significantly reduced by diluting the premixed fuel gas.
However, since the flame is conductive, there is a greater possibility that the flame will enter the premixer and flash back or blow off. On the other hand, practically, flame stabilization technology for premixed combustion and improvement of combustion safety are desired.

As shown in FIG. 2, a flame holding method for stably holding the flame is to place a structure downstream of the premixer outlet to hold the flame by utilizing the wake of the structure, or to step the outlet. There is a method shown in FIG. 3 in which a high temperature burned gas is retained by creating a circulating flow by rapidly providing a flow path. The former method is called bluff body type flame holding, and the latter method is called recess type flame holding.

Premixed Combustion A small amount of fuel is required for starting and stopping a practical gas turbine combustor and during low load combustion. At this time, if the premixed combustion is adopted, the flow velocity of the premixed fuel gas becomes small, so that the risk of flashback into the premixer increases. A pilot burner that performs diffusion combustion is used to start and stop, and the proportion of diffusion combustion and premixed combustion is changed according to the load.

In the ignition of the premixed fuel gas at the start of the premixed combustion, it is advantageous for the recess type flame stabilizer capable of forming a large and stable circulation flow to maintain the high temperature region. When the load is large, the bluff body type flame holding with a wide flame surface formed in the wake of the object is more likely to have a premixed gas and a high temperature burned gas newly supplied from the premixer. This is advantageous because the contact surface of is increased. As a conventional example, paying attention to the shape of the flame stabilizer as described in JP-A-4-103906, in particular, the flame stabilizer is made into a structure having an acute-angled corner, and the flame base is attached to the corner to improve the flame-retention performance. There is an example of improving.

[0007]

In the conventional example, when the recess type structure is provided, it is advantageous to ignite the premixed air-fuel mixture, but the flame is easily blown off at the time of high load combustion. In this case, if a bluff body type flame stabilizer is adopted, ignition may not normally occur. No consideration has been given to the structure of the flame stabilizer that simultaneously fulfills the flame holding function of normally igniting and at the same time being able to withstand high-load combustion.

On the other hand, in the conventional example, the flame stabilizer has a cooling system such as a cooling plate or air cooling in order to prevent the temperature rise due to the flame, but the flame stabilizer burnout due to the abnormal temperature rise of the flame stabilizer is detected. No measures are taken. Further, when the flame stabilizer is burned out, the combustor may be damaged, but no means for avoiding this is considered.

An object of the present invention is to provide a gas turbine combustor having a flame stabilizer which is easily ignited by a premixed gas, stably holds a flame during high-load combustion, and is suitable for avoiding burnout. .

[0010]

A first gas turbine combustor according to the present invention is a gas turbine combustor having a premixer, wherein the premixer is a movable retainer capable of changing a flame holding state. A gas turbine combustor characterized in that a flamer is provided at the outlet, and the flame stabilizer is provided with a cooling means. In order to achieve the above object, in the present invention, when igniting the premixed fuel gas by the flame of the pilot burner, a recess type flame holding form is adopted, and a bluff body type flame holding form is set under partial load or high load. Move the flame stabilizer provided at the premixer outlet so that it will be removed.

A second gas turbine combustor of the present invention is the gas turbine combustor of the first gas turbine combustor, wherein the flame stabilizer is provided with a sensor section for measuring the temperature of the flame stabilizer.

[0012]

According to the first gas turbine combustor, the recess type flame holding is provided at the time of ignition. The expansion ratio of the flow path at the premixer outlet is increased by the combustion chamber cylinder wall and the flame stabilizer, and a long and stable circulation flow is formed behind the step composed of the flame stabilizer and the combustion chamber cylinder wall. It becomes possible to do. If the circulation flow is large, the burned gas is likely to be retained, and the fire of the pilot burner can be quickly guided to the premixed fuel gas. When the flame stabilizer is moved in the premix fuel flow at the outlet of the premixer, it switches to the bluff body type flame stabilizer. During high-load combustion, multiple flame surfaces extend in the wake region of the flame stabilizer placed in the main stream, and the premixed fuel gas exits the premixer and burns immediately, completing combustion in a short combustion range. Will be done.

According to the second gas turbine combustor, the flame holding at the start of premixed combustion is confirmed based on the flame holding temperature detected by the sensor portion provided in the flame holding unit, and the recess type flame holding is confirmed. It is possible to control the output of premixed combustion by determining the timing of switching from bluff body type flame holding, controlling the position of the flame stabilizer, and controlling the pilot burner or premixed fuel gas flow rate. This enhances the practicality of the first gas turbine combustor. Also, an abnormal temperature rise of the flame stabilizer due to factors such as the cooling system not working properly can be detected from the temperature measured by the sensor unit, and the output of premixed combustion is temporarily reduced to reduce flame holding. It is also possible to avoid burnout of the vessel. Furthermore, burnout of the flame stabilizer immediately leads to burnout of the sensor unit.Therefore, burnout of the flame stabilizer is detected due to an abnormal response of the measurement of the sensor unit, and combustion of the flame stabilizer before damage to the premixer or combustor is detected. Can detect abnormalities.

[0014]

Embodiments of the present invention will be described below with reference to the accompanying drawings.

FIG. 1 shows a first embodiment of the gas turbine combustor of the present invention. The fuel gas 101 led from the fuel supply pipe 17 for the pilot burner is the air 10 for the pilot burner.
At the pilot burner outlets of 1 and 15, they contact each other, diffuse combustion, and form a diffusion flame 106. On the other hand, the space around the pilot burner and the cylindrical wall outside the pilot burner is used as the premixer 1.
Set to 1. Fuel 1 for premix combustion in the premixer 11
8 and a part 103 of the air 102 sent from the compressor are mixed. The air-fuel mixture is ignited by the high-temperature burned gas behind the flame stabilizer 12 provided near the outlet of the premixer 11 to form a premixed flame.

The flame stabilizer 12 is supported by a column 14 which also serves as a cooling air introduction pipe, and the column can move in the longitudinal direction of the premixer. Further, the flame stabilizer is cooled by passing the cooling air 101 introduced and discharged by the column 14 through the cavity inside the flame stabilizer.

As shown in FIG. 4, when the flame stabilizer 12 is located at the outlet of the flame stabilizer, a recess type retainer in which a circulating flow is formed at a corner formed by the flame stabilizer and the side wall of the combustion chamber. Become a flame. In this case, the size of the rapidly expanding portion formed on the inner cylinder side of the combustor is increased by the amount corresponding to the flame stabilizer, so that the size of the circulation flow region is increased.
Since this circulating flow is relatively stable, high temperature burned gas is easily retained. During ignition of the premixed fuel gas, the pilot flame 106 is easily guided by the pilot burner, and stable ignition can be performed. Once the ignition is performed and the premixed flame is formed, the position of the flame stabilizer is moved to the combustion chamber 109 side to switch to the bluff body type flame stabilization as shown in FIG. In this case, the high-temperature burned gas is retained by the flame stabilizer wake that extends into the combustion chamber 109, and the region where the high-temperature burned gas and the newly introduced premixed fuel gas come into contact with each other is large, so that the premixed fuel gas quickly flows. Ignite and burn. Therefore, the combustion area becomes smaller,
This is advantageous for downsizing the combustor. Also, in this example,
Even when switching to the bluff body type flame holding, there is still a circulation region for holding the high-temperature burned gas in the sudden expansion portion, and the flame holding role is sufficiently fulfilled.

A second embodiment of the present invention is shown in FIG. The temperature distribution of the flame stabilizer is detected by measuring the temperature of the flame stabilizer by the temperature measuring unit 41, and the flame base of the flame stabilizer moves away from the flame stabilizer to make combustion unstable. Can be detected. It is possible to optimize the flow rate of the cooling fluid based on the measured value and avoid burnout of the flame stabilizer. By providing a plurality of temperature measuring units 41, it is possible to correct the decrease in the measured temperature due to the cooling fluid and to know the temperature distribution of the flame stabilizer with high accuracy. Further, when the temperature measuring unit 41 is arranged in the vicinity of the flame base, if the flame stabilizer is burned out, the temperature measuring unit 41 is simultaneously operated.
Is burned out and reflected in the abnormal response obtained from the temperature measuring unit 41. The temperature measuring unit 41 can be realized by using, for example, a thermocouple.

[0019]

According to the present invention, the ignition of the premixed gas by the pilot burner can be stabilized, and the flame holding suitable for high load combustion can be performed. Further, burnout of the premixer and the gas turbine combustor due to abnormal combustion can be avoided.

[Brief description of drawings]

FIG. 1 is a sectional view showing a first embodiment of a gas turbine combustor having a premixer provided with a flame stabilizer according to the present invention.

FIG. 2 is a cross-sectional view showing a conventional example of a bluff body type flame stabilizer.

FIG. 3 is a sectional view showing a conventional example of a recess-type flame stabilizer.

FIG. 4 is a cross-sectional view showing the position of the flame stabilizer and the state of combustion when starting and stopping premix combustion of the flame stabilizer according to the present invention.

FIG. 5 is a cross-sectional view showing the position and combustion state of the flame stabilizer during high-load combustion of the flame stabilizer according to the present invention.

FIG. 6 is a sectional view showing a second embodiment of a gas turbine combustor having a premixer provided with a flame stabilizer according to the present invention.

[Explanation of symbols]

11 ... Premixer, 12 ... Flame stabilizer, 13 ... Fuel supply pipe, 1
4 ... Flame stabilizer support column, 15 ... Pilot burner outlet, 16
... Air supply pipe for pilot burner, 17 ... Fuel supply pipe for pilot burner, 18 ... Fuel for premix combustion, 19 ... Premixture, 101 ... Pilot flame, 102 ... Compressed air,
103 ... Air for premixed combustion, 104 ... Air for cooling film, 10
5 ... Premixed flame, 106 ... Pilot burner flame, 10
7 ... Combustor outer cylinder, 108 ... Combustor inner cylinder, 109 ... Combustion chamber, 110 ... Premixer inner cylinder wall, 111 ... Premixer outer cylinder wall.

Claims (2)

[Claims]
1. A gas turbine combustor having a premixer for premixing air and fuel, wherein the premixer is provided with a movable flame stabilizer capable of changing a flame holding state at an outlet thereof. A gas turbine combustor, characterized in that the reactor is provided with a cooling means.
2. The gas turbine combustor according to claim 1, wherein the flame stabilizer is provided with a sensor section for measuring the temperature of the flame stabilizer.
JP14885893A 1993-06-21 1993-06-21 Gas turbine combustor Pending JPH074661A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP14885893A JPH074661A (en) 1993-06-21 1993-06-21 Gas turbine combustor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP14885893A JPH074661A (en) 1993-06-21 1993-06-21 Gas turbine combustor

Publications (1)

Publication Number Publication Date
JPH074661A true JPH074661A (en) 1995-01-10

Family

ID=15462319

Family Applications (1)

Application Number Title Priority Date Filing Date
JP14885893A Pending JPH074661A (en) 1993-06-21 1993-06-21 Gas turbine combustor

Country Status (1)

Country Link
JP (1) JPH074661A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5768098A (en) * 1996-02-27 1998-06-16 Kabushiki Kaisha Toshiba Portable electronic apparatus having receptacle for detachably storing card-type electronic component
US6244894B1 (en) 1999-03-02 2001-06-12 Nec Corporation Cellular phone battery equipped with IC card

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5768098A (en) * 1996-02-27 1998-06-16 Kabushiki Kaisha Toshiba Portable electronic apparatus having receptacle for detachably storing card-type electronic component
US6244894B1 (en) 1999-03-02 2001-06-12 Nec Corporation Cellular phone battery equipped with IC card

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