CN214581226U

CN214581226U - Multi-fuel gas turbine

Info

Publication number: CN214581226U
Application number: CN202022647803.XU
Authority: CN
Inventors: 靳普
Original assignee: Individual
Current assignee: Liu Muhua
Priority date: 2020-11-16
Filing date: 2020-11-16
Publication date: 2021-11-02
Anticipated expiration: 2030-11-16

Abstract

The utility model discloses a gas turbine with a plurality of fuel nozzles, which comprises an air compressor, a motor, a turbine and a combustion chamber, wherein the side wall of the combustion chamber is fixed with a hollow evaporating pipe; the fuel nozzle communicated with the tail end of the fuel pipeline penetrates through the side wall of the combustion chamber to enter the combustion chamber and extends into the evaporation pipe; at least two fuel nozzles are accommodated in the evaporation tube; accordingly, the number of fuel conduits is the same as the number of fuel nozzles; the number of the evaporating pipes is two or more, and the evaporating pipes are uniformly arranged around the axis of the rotating shaft of the gas turbine. The evaporating pipe is I-shaped or T-shaped. The utility model discloses a gas turbine sets up a plurality of fuel injector inside the evaporating pipe, provides many fuel supply channel promptly, can spray different types of fuel burning at different periods to adapt to multiple operating mode.

Description

Multi-fuel gas turbine

Technical Field

The utility model relates to a many fuel gas turbine.

Background

The evaporating pipe type nozzle of gas turbine is characterized by that it uses lower pressure to spray oil into evaporating pipe in direct-injection mode, the gas around the evaporating pipe and burnt gas in the combustion chamber can be used for heating fuel gas, and the fuel oil can be evaporated and mixed initially, and the formed gaseous rich-oil mixed gas can be fed into the combustion chamber, mixed with air flow of main combustion hole and combusted. The existing fuel nozzle is a single fuel nozzle, the requirement on the fuel type is high, and if the fuel is lack, the operation has to be stopped.

Disclosure of Invention

To the above-mentioned prior art, the utility model provides a multi-fuel gas turbine, it holds in the evaporating pipe and sets up two at least fuel nozzle, and the fuel pipeline is more than two, can spray different kinds of fuel burning in different periods to adapt to multiple operating mode.

The utility model discloses a realize through following technical scheme:

a multi-fuel gas turbine comprises an air compressor, a starting integrated motor, a turbine and a combustion chamber, wherein a hollow evaporation pipe is fixed on the side wall of the combustion chamber; the fuel nozzle communicated with the tail end of the fuel pipeline penetrates through the side wall of the combustion chamber to enter the combustion chamber and extends into the evaporation pipe; at least two fuel nozzles are accommodated in the evaporation tube; accordingly, the number of fuel conduits is the same as the number of fuel nozzles.

The evaporating pipes are arranged into two or more than two and are uniformly arranged around the central axis of the gas turbine.

Furthermore, the evaporating pipe is I-shaped, forms an included angle with the side wall of the combustion chamber, extends into the combustion chamber in an inclined mode, one end of the evaporating pipe is fixed, the other end of the evaporating pipe is suspended, and the suspended end of the evaporating pipe is flared.

Furthermore, the evaporating pipe is T-shaped, and obliquely extends into the combustion chamber at an included angle with the side wall of the combustion chamber 11, one end of the evaporating pipe is fixed, the other end of the evaporating pipe is suspended, the suspended end is T-shaped and connected with another short pipe, the short pipe is orthogonally communicated with the oblique evaporating pipe, and two ends of the short pipe are through.

Further, the oil spray hole at the tail end of the fuel nozzle is parallel to the axis of the evaporation pipe.

Furthermore, resistance wires are wound on the outer wall of the evaporation tube.

The evaporating pipe and the fuel nozzle are made of ceramics or high-temperature alloy, and the evaporating pipe made of the high-temperature alloy needs to be subjected to corresponding surface oxidation treatment, so that certain characteristics of high temperature resistance and corrosion resistance are ensured.

The utility model discloses a gas turbine sets up two or more fuel nozzles in the evaporating pipe inside, correspondingly, sets up more than two fuel pipes, namely provides many fuel supply channels, can spray different kinds of fuel combustion in different periods of time to adapt to multiple operating mode; the outside of the evaporating pipe is provided with a resistance wire, the evaporating pipe can be heated in the starting stage, and the fuel can be atomized and evaporated under the condition of no fuel gas heating.

The utility model discloses an evaporating pipe overall arrangement is inside combustion chamber flame tube, and the during operation leans on combustion chamber high temperature gas or preheats air and fuel mixture in the resistance wire heating tube, makes fuel atomization evaporation, becomes the gaseous fuel of easily burning, and the burning is more abundant.

The utility model discloses a gas turbine still has following advantage:

1. the whole combustion chamber is simple and compact in layout, and both the flow resistance loss and the heat loss are low.

2. The evaporation tube and the fuel nozzle have strong applicability to fuels, and are suitable for various fuels such as gasoline, kerosene, methanol, ethanol (and other biomass fuels).

3. Oil and gas in the evaporation tube are uniformly mixed, so that a local oil-rich area of the main combustion area is avoided, and smoke and carbon deposition are reduced.

4. When the fuel is burnt, the flame is blue, the radiant heat is less, and the wall temperature of the flame tube is lower.

5. The evaporating pipe does not require high oil supply pressure, and the temperature field distribution of the outlet of the combustion chamber is uniform and stable.

6. The oil supply pipe is simplified.

The various terms and phrases used herein have the ordinary meaning as is well known to those skilled in the art. To the extent that the terms and phrases are not inconsistent with a known meaning, the meaning of the present invention is expressed, the specification is set forth.

Drawings

Fig. 1 is a schematic structural view of a gas turbine according to the present invention.

FIG. 2 is a first schematic view of the evaporator tube (type I) and the fuel nozzle.

FIG. 3 is a second schematic view of the structure of the evaporator tube (type I) and the fuel nozzle.

Fig. 4 is a third schematic structural view of the evaporation tube (T-shaped) and the fuel nozzle.

The system comprises a gas turbine 1, a combustion chamber 11, a fuel pipeline 12, a fuel nozzle 13, an oil spray hole 131, an evaporation pipe 14, an air compressor 102, an integrated motor 103 and a starting turbine 104.

Detailed Description

The present invention will be further described with reference to the accompanying drawings. However, the scope of the present invention is not limited to the following examples. Those skilled in the art will appreciate that various changes and modifications may be made to the invention without departing from the spirit and scope of the invention.

Example 1

A multi-fuel gas turbine comprises an air compressor 102, a starting integrated motor 103, a turbine 104 and a combustion chamber 11, as shown in figure 1, wherein a hollow evaporation pipe 14 is fixed on the side wall of the combustion chamber 11; the fuel nozzle 13 communicated with the tail end of the fuel pipe 12 penetrates through the side wall of the combustion chamber 11 to enter the combustion chamber 11 and extends into the evaporation pipe 14; at least two fuel nozzles 13 are accommodated in the evaporating tube 14; accordingly, the number of fuel pipes 12 is the same as the number of fuel nozzles 13.

The evaporating pipes 14 are provided in two or more numbers, and are uniformly arranged around the axis of the gas turbine shaft.

In one mode, the evaporation tube 14 is I-shaped, and as shown in fig. 2 and 3, it extends into the combustion chamber 11 at an angle with the side wall of the combustion chamber 11, and one end of the evaporation tube is fixed, the other end of the evaporation tube is suspended, and the suspended end is flared.

Alternatively, the evaporating tube 14 is T-shaped, and as shown in fig. 4, it extends into the combustion chamber 11 at an angle with the side wall of the combustion chamber 11, and one end of it is fixed, and the other end is suspended, and the suspended end is T-shaped and connected to another short tube, which is orthogonally communicated with the inclined evaporating tube, and two ends of the short tube are through.

During the specific application, determine evaporating pipe 14 to be I type or T type according to actual demand, guarantee that the atomizing evaporation is complete, the flow resistance loss is little.

Further, the oil spray holes 131 at the end of the fuel nozzle 13 are parallel to the axis of the evaporating tube 14.

Further, resistance wires are wound on the outer wall of the evaporation tube 14.

The above examples are provided to those of ordinary skill in the art to fully disclose and describe how to make and use the claimed embodiments, and are not intended to limit the scope of the disclosure herein. Modifications apparent to those skilled in the art are intended to be within the scope of the appended claims.

Claims

1. The utility model provides a many fuel gas turbine, includes air compressor machine, motor, turbine and combustion chamber, its characterized in that: a hollow evaporation tube is fixed on the side wall of the combustion chamber; the fuel nozzle communicated with the tail end of the fuel pipeline penetrates through the side wall of the combustion chamber to enter the combustion chamber and extends into the evaporation pipe; at least two fuel nozzles are accommodated in the evaporation tube; accordingly, the number of fuel conduits is the same as the number of fuel nozzles.

2. The multi-fuel gas turbine engine of claim 1, wherein: the number of the evaporating pipes is two or more, and the evaporating pipes are uniformly arranged around the axis of the rotating shaft of the gas turbine.

3. The multi-fuel gas turbine engine of claim 1, wherein: the evaporating pipe is I-shaped, and obliquely extends into the combustion chamber at an included angle with the side wall of the combustion chamber, one end of the evaporating pipe is fixed, the other end of the evaporating pipe is suspended, and the suspended end is flared and expanded.

4. The multi-fuel gas turbine engine of claim 1, wherein: the evaporating pipe is T-shaped, forms an included angle with the side wall of the combustion chamber and obliquely extends into the combustion chamber, one end of the evaporating pipe is fixed, the other end of the evaporating pipe is suspended, the suspended end is T-shaped and is connected with another short pipe, the short pipe is orthogonally communicated with the oblique evaporating pipe, and the two ends of the short pipe are through.

5. The multi-fuel gas turbine as claimed in claim 1 or 3 or 4, wherein: and the oil spray hole at the tail end of the fuel nozzle is parallel to the axis of the evaporation tube.

6. The multi-fuel gas turbine engine of claim 1, wherein: and a resistance wire is wound on the outer wall of the evaporation tube.