JP2004150779A - Gas turbine combustor - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To miniaturize and simplify a gas turbine whole body by making a narrow and long structure into the thick and short one in an annular combustor for a micro gas turbine. <P>SOLUTION: This gas turbine combustor is provided with a recessed cross sectional liner whose combustion gas upstream part is formed radially inward in a meridian cross section of the annular combustor liner, combustion gas midstream part is bent into a U-shape and combustion gas downstream part is formed radially outward. <P>COPYRIGHT: (C)2004,JPO

Description

[0001]
TECHNICAL FIELD OF THE INVENTION
The present invention relates to an annular combustor for a micro gas turbine device.
[0002]
[Prior art]
Conventional gas turbine combustors are generally classified into a can type, an annular type, and an annular can type. The can type is further classified into a single can type and a multi-can type in which a plurality of the same can types are arranged circumferentially.
FIG. 2 shows a schematic diagram of a typical annular combustor. The combustion gas passage in the liner in the meridional section has a linear structure substantially parallel to the axial direction. Compared with other types of combustors, such annular combustors have advantages such as a smaller structure, a smaller pressure loss, and easier fire-burning, but also have an optimal fuel and air flow pattern. However, there is a disadvantage that the gas temperature distribution at the outlet is difficult to be uniform. The disadvantage is more pronounced when the length of the combustion gas passage is small compared to the passage cross-sectional area, that is, in the case of a short and long annular structure. Therefore, compared with the axial flow type gas turbine, the radial flow type is adopted as the stage of the compressor and turbine, and the compressed air intake pipe and the combustion gas discharge pipe are used as the combustor of the micro gas turbine with a short shaft length. Single cans are often used despite their complicating drawbacks. A design that avoids the drawbacks of the single can type and dare to adopt the annular type results in an elongated combustor that extends long in the axial direction to the downstream of the turbine stage, resulting in an increase in the overall length of the gas turbine.
[0003]
[Problems to be solved by the invention]
SUMMARY OF THE INVENTION An object of the present invention is to provide a micro gas turbine device with the above-described problem that arises when the conventional combustor-related technology is applied, that is, a complicated structure in which a compressed air intake pipe and a combustion gas exhaust pipe in a single can type are complicated. It is an object of the present invention to provide a simple and short annular combustor that solves the problem of elongation of the structure of the annular type while avoiding the formation of a ring.
[0004]
[Means for Solving the Problems]
The present invention relates to a combustor of a heat cycle power generation device using a gas turbine device, a waste heat boiler device, and a back pressure turbine device (reference numeral 2 in Japanese Patent Application No. 2000-132975).
FIG. 1 shows an assembly cross-sectional view of the apparatus when the present invention is applied to FIG. 1 is a combustor liner, 2 is a fuel injection nozzle, 3 is a combustion air hole, 4 is a dilution air hole, 5 is a dilution steam / air hole, 6, 7, and 8 are gas turbine casings and combustor outer tubes, respectively. Mutually tightened by bolts. Reference numeral 9 denotes an air flow regulating plate, 10 denotes an air / steam isolation tube, 11 denotes a bearing housing, 12 denotes a compressed air inlet, 13 denotes a steam inlet, and 14 denotes a combustion gas outlet.
FIG. 3 shows the appearance of the combustor liner 1;
FIG. 4 shows an appearance in a state where the combustor liner 1 is incorporated in a casing 7 to which the injection nozzle 2 is attached. Compressed air for combustion and dilution is guided to a space outside the combustor liner 1 from a compressed air inlet 12 opened in the gas turbine casing 6, and flows into the outer peripheral side and the inner peripheral side of the liner 1 in two parts. . Fuel is injected radially inward from the fuel injection nozzle 2 into the liner 1, and is combined with combustion air entering through the combustion air holes 3 and burns. The ignition plug is provided at one position on the outermost peripheral surface of the liner 1. The compressed air flowing on the outer peripheral side of the liner 1 passes between the straightening plate 9 and the liner 1, and a part of the compressed air enters the liner 1 from the combustion air hole 3 as combustion air, and the remainder is dilution air as dilution air. More into the liner 1. The compressed air flowing on the inner peripheral side of the liner 1 passes between the casing 6 and the liner 1, further passes between the isolation cylinder 10 and the liner 1, and partly as combustion air into the liner 1 from the combustion air hole 3 on the way. Mixed, the remainder being dilution air. The dilution steam passes through the inside of the isolation cylinder 10 through a steam inlet 13 opened in the gas turbine casing 6 and mixes with dilution air passing through the inner peripheral side of the liner 1, and then the dilution steam / air hole 5. More into the liner 1. The combustion gas generated in the upstream part and the middle part in the liner 1 is mixed with the dilution air and the dilution steam in the liner downstream part and guided to the combustion gas outlet 14.
[0005]
BEST MODE FOR CARRYING OUT THE INVENTION
Assembly sectional view of the entire power generation device when the present invention is applied to a combustor (reference numeral 2 in Japanese Patent Application No. 2000-132975) of a heat cycle power generation device using a gas turbine device, a waste heat boiler device, and a back pressure turbine device. Is shown in FIG. Reference numeral 15 denotes an air compressor stage, 16 denotes a back-pressure steam turbine wheel, and 17 denotes a turbine stage.
[0006]
【The invention's effect】
When the distance between the outer peripheral surface and the inner peripheral surface of the liner is large in the annular type combustor, combustion air, dilution air, and steam can be uniformly mixed near the center of the liner under appropriate pressure loss. Therefore, the gas temperature distribution at the outlet is not uniform. Further, in a liner in which the combustion gas passage is short in the flow direction, the gas passing time required for combustion and mixing cannot be obtained, and the combustion gas reaches the outlet with insufficient combustion or mixing.
Combustion air and dilution air / steam by the structure of the present invention with the combustion gas upstream in the meridional section of the annular liner radially inward, the U-turn in the combustion gas midstream, and the combustion gas downstream in the radially outward direction Reaches the center, the combustion gas passage lengthens in the flow direction, and a sufficient transit time for combustion and mixing can be obtained. As a result, a combustor that has a uniform outlet gas temperature distribution and high combustion efficiency and can be accommodated in a short and wide structural space is obtained. Such a combustor greatly contributes to simplification of the overall structure of the micro gas turbine and miniaturization.
In addition, the structure in which the fuel injection nozzle 2 is mounted radially inward from the outer surface of the casing 7 on the outermost peripheral surface of the liner 1 at the outermost peripheral portion of the combustion gas facilitates replacement inspection work of the fuel injection nozzle 2.
The flow of combustion and dilution air is rectified before entering the liner 1 by the donut-shaped flat plate rectifying mechanism 9 attached to the center of the hollow space outside the outer peripheral surface of the liner 1, so that the liner 1 is cooled more effectively than the outer peripheral surface. I do.
When the present invention is used as a combustor (reference numeral 2 in Japanese Patent Application No. 2000-132975) of a heat cycle power generation device using a gas turbine device, a waste heat boiler device, and a back pressure turbine device, the inner peripheral side of the liner 1 is used. Is provided with an isolation cylinder 10 for isolating the mixed steam and the combustion air to prevent a large amount of steam from being mixed into the combustion air and deteriorating the combustion performance.
[Brief description of the drawings]
1 is an assembled sectional view of a combustor according to the present invention;
[Claims]
Claim 1 will be described more.
FIG. 2 is a schematic view of a conventional annular combustor. The left figure shows the meridional section, and the right figure shows a part of the circular section perpendicular to the meridian section in the circumferential direction.
3 is an external view of the combustor liner 1. FIG. 4 is an external view of the combustor liner 1 incorporated in a casing 7 to which the injection nozzle 2 is attached. FIG. 5 is a gas turbine device and a waste heat boiler device according to the present invention. Cross-sectional view of the entire power generator when applied to the combustor of a heat cycle power generator using a power and back pressure turbine device [Description of Signs]
1 is a combustor liner, 2 is a fuel injection nozzle, 3 is a combustion air hole, 4 is a dilution air hole, 5 is a dilution steam / air hole, 6, 7, and 8 are gas turbine casings and combustor outer cylinders, 9 Is an air straightening plate, 10 is an air / steam separating tube, 11 is a bearing housing, 12 is an air inlet, 13 is a steam inlet, 14 is a combustion gas outlet, 15 is an air compressor paragraph, and 16 is back pressure steam. The turbine wheel 17 indicates a turbine stage.

Claims (7)

Regarding the annular combustor used for gas turbines and the like, the meridional section of the liner has a concave cross section in which the combustion gas upstream portion is radially inward, the U-turn is in the combustion gas midstream portion, and the combustion gas downstream portion is radially outward. Device with liner A device for mounting a plurality of fuel injection nozzles radially inward at equal circumferential intervals on the outermost peripheral surface of the liner in the upstream portion of the combustion gas Apparatus having a donut-shaped flat plate rectifying mechanism in the center of the hollow space outside the liner outer peripheral surface Apparatus having an isolating cylinder for isolating mixed steam and combustion air in a space on the axial center side of the inner peripheral surface of the liner

Images