Micro gas turbine oil supply system suitable for low-temperature environment and multi-fuel nozzle

Abstract

The invention aims to provide a micro gas turbine oil supply system and a multi-fuel nozzle suitable for a low-temperature environment, the micro gas turbine oil supply system comprises a flame tube outer cylinder, a flame tube inner cylinder, an oil transportation header pipe and an oil transportation branch pipe, the flame tube outer cylinder is mounted outside the flame tube inner cylinder, and a combustion chamber is formed between the flame tube outer cylinder and the flame tube inner cylinder; a flame tube outer tube oil supply interlayer is arranged in the flame tube outer tube, an oil conveying header pipe is communicated with the flame tube outer tube oil supply interlayer, an oil conveying branch pipe is arranged on the flame tube outer tube, one end of the oil conveying branch pipe is communicated with the flame tube outer tube oil supply interlayer, and an oil spraying nozzle is installed at the other end of the oil conveying branch pipe and located in a combustion chamber. By reasonably arranging the structures such as the oil conveying main pipe and the oil conveying branch pipes, the structural strength of the flame tube is enhanced, waste heat of the flame tube is fully utilized for preheating fuel oil, meanwhile, the fuel oil is utilized for cooling the tube wall of the flame tube, and the effect of enhancing the starting performance in the low-temperature environment is achieved.

Description

Technical Field

[0001] The present invention relates to a gas turbine, specifically a micro gas turbine. Background Art

[0002] The combustion chamber of a micro gas turbine is a combustion device made of high-temperature resistant alloy materials and is one of the essential components in a gas turbine engine. It is located between the compressor and the turbine and is responsible for converting the chemical energy of the fuel into heat energy through combustion chemical reactions to form high-temperature and high-pressure combustion products to drive the turbine to do work.

[0003] When using a micro gas turbine in a low-temperature environment, the conventional fuel supply system of the micro gas turbine has problems such as difficult startup and poor operation continuity in a low-temperature environment due to the increased viscosity of the fuel and the increased pressure demand in a low-temperature environment. Summary of the Invention

[0004] The purpose of the present invention is to provide a fuel supply system and a multi-fuel nozzle for a micro gas turbine applicable to a low-temperature environment that can solve problems such as startup and operation of the micro gas turbine under low-temperature conditions.

[0005] The purpose of the present invention is achieved as follows:

[0006] A fuel supply system and a multi-fuel nozzle for a micro gas turbine applicable to a low-temperature environment according to the present invention are characterized in that: it includes an outer barrel of the flame tube, an inner barrel of the flame barrel, a main fuel pipeline, and a branch fuel pipeline. The outer barrel of the flame tube is installed outside the inner barrel of the flame barrel. A combustion chamber is formed between the outer barrel of the flame tube and the inner barrel of the flame barrel. An oil supply sandwich layer of the outer barrel of the flame tube is arranged inside the outer barrel of the flame tube. The main fuel pipeline communicates with the oil supply sandwich layer of the outer barrel of the flame tube. The branch fuel pipeline is arranged on the outer barrel of the flame tube. One end of the branch fuel pipeline communicates with the oil supply sandwich layer of the outer barrel of the flame tube, and the other end is installed with an injector nozzle, and the injector nozzle is located in the combustion chamber.

[0007] The present invention may further include:

[0008] 1. The installation positions of the main fuel pipeline and the branch fuel pipeline are respectively on the head and tail sides of the outer barrel of the flame tube, so that the fuel flows from the main fuel pipeline through the oil supply sandwich layer of the outer barrel of the flame tube and then enters the injector nozzle from the branch fuel pipeline.

[0009] 2. A swirler is arranged beside the injector nozzle.

[0010] 3. The branch fuel pipeline includes at least two and is evenly arranged on the circumference of the outer barrel of the flame tube.

[0011] 4. Air holes are arranged on the barrel walls of the outer barrel of the flame tube and the inner barrel of the flame barrel.

[0012] 5. The diameters between the air holes are different.

[0013] The advantages of the present invention are as follows: By reasonably arranging structures such as the main fuel pipeline and the fuel pipeline branches, the structural strength of the combustion chamber liner is enhanced. While fully utilizing the waste heat of the flame tube to preheat the fuel oil, the fuel oil is used to cool the wall of the flame tube, achieving the effect of enhancing the starting performance in a low-temperature environment. By designing six evenly distributed fuel injectors combined with a swirler and the combination with air holes, not only can the fuel oil be fully atomized, but also the intake of high-pressure air can be ensured, enabling the fuel oil to burn fully, increasing the thermal efficiency of the device, and ensuring the stability and continuity of the combustion cycle. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 is a schematic structural diagram of the present invention (one side of the tail);

[0015] Figure 2 is a schematic structural diagram of the present invention (one side of the head);

[0016] Figure 3 is a cross-sectional view of the present invention (one side of the tail);

[0017] Figure 4 is a cross-sectional view of the present invention (one side of the head);

[0018] Figure 5 is a side cross-sectional view of the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0019] The present invention will be described in more detail with reference to the accompanying drawings as follows:

[0020] Combined with Figures 1-5 , a fuel supply system and a multi-fuel nozzle for a micro gas turbine applicable to a low-temperature environment according to the present invention include an outer combustion chamber liner 1, an inner combustion chamber liner 2, an outer combustion chamber liner fuel supply sandwich layer 3, a main fuel pipeline 4, fuel pipeline branches 5, a swirler 6, a fuel injector 7, and air holes 8. A combustion chamber is formed between the outer combustion chamber liner 1 and the inner combustion chamber liner 2. The main fuel pipeline 4 is connected to the outer combustion chamber liner fuel supply sandwich layer 3, and the interface is behind the combustion chamber liner. The outer combustion chamber liner fuel supply sandwich layer 3 is simultaneously connected to the fuel pipeline branches 5. The swirler 6 and the fuel injector 7 are installed at the outlet of the fuel pipeline branches 5, and the air holes 8 are evenly distributed on the wall of the combustion chamber liner.

[0021] The main fuel pipeline 4 is arranged at the tail, and the fuel oil is evenly divided through the outer combustion chamber liner fuel supply sandwich layer 3. Through the entire outer combustion chamber liner 1, the heat of the outer combustion chamber liner 1 is used to preheat the fuel oil, changing the physical properties of the fuel oil and making it easier to mix with the high-pressure air entering the combustion chamber liner for full combustion.

[0022] By arranging the outer combustion chamber liner fuel supply sandwich layer 3, the function of cooling the wall of the combustion chamber liner is achieved.

[0023] By arranging air holes 8 with different diameters to be evenly distributed on the wall surface of the combustion chamber, it is convenient for the high-pressure air outside to enter the combustion chamber for mixing and cooling, thereby cooling and protecting the wall surface.

[0024] The outer cylinder 1 of the combustion chamber adopts a double-layer structure, forming an oil supply sandwich layer 3 for the outer cylinder of the combustion chamber, which cools the wall surface of the combustion chamber and at the same time plays a supporting role for the entire combustion chamber, strengthening the structural strength.

[0025] The high-pressure gas is input in a manner combining a swirler 6 and air holes 8. The swirler 6 is arranged beside the fuel injector 7, so that the injected fuel is dispersed and fully mixed with the incoming high-pressure gas for combustion, ensuring the uniformity and stability of fuel supply.

[0026] Specifically, during operation, first, the fuel enters the oil supply sandwich layer 3 of the outer cylinder of the combustion chamber through the oil delivery main pipe 4 located at the tail. After flowing through the entire flame tube, the fuel is preheated and then evenly flows into the oil delivery branch pipe 5, is pressurized and enters the fuel injector 7, and is fully mixed with the high-pressure air entering the combustion chamber through the swirler 6 and air holes 8 for combustion, completing an oil supply cycle.

Claims

1. A micro gas turbine oil supply system and multi-fuel nozzle suitable for low temperature environment, characterized by: It includes a flame tube outer tube, a flame barrel inner tube, an oil main pipe, and an oil branch pipe. The flame tube outer tube is installed on the outside of the flame barrel inner tube. A combustion chamber is formed between the flame tube outer tube and the flame barrel inner tube. An outer tube oil supply interlayer is arranged inside the flame tube outer tube. The oil main pipe is communicated with the flame tube outer tube oil supply interlayer. An oil branch pipe is arranged on the flame tube outer tube. One end of the oil branch pipe is connected to the flame tube outer tube oil supply interlayer, and a fuel injector is installed on the other end. The fuel injector is located in the combustion chamber.

2. The micro gas turbine oil supply system and multi-fuel nozzle suitable for low temperature environment according to claim 1, characterized in that: The installation positions of the oil main pipe and the oil branch pipe are respectively on the head and tail sides of the flame tube outer tube, so that the fuel flows from the oil main pipe through the flame tube outer tube oil supply interlayer and then enters the fuel injector from the oil branch pipe.

3. The micro gas turbine oil supply system and multi-fuel nozzle suitable for low temperature environment according to claim 1, characterized in that: A swirler is provided next to the fuel injector.

4. The micro gas turbine oil supply system and multi-fuel nozzle suitable for low temperature environment according to claim 1, characterized in that: The oil delivery branch pipes include at least two and are evenly arranged on the circumference of the outer cylinder of the flame tube.

5. The micro gas turbine oil supply system and multi-fuel nozzle suitable for low temperature environment according to claim 1, characterized in that: Air holes are arranged on the walls of the outer tube of the flame tube and the inner tube of the flame barrel.

6. The micro gas turbine oil supply system and multi-fuel nozzle suitable for low temperature environment according to claim 5, characterized in that: The diameters of the air holes vary from one air hole to another.

Images