WO2023065851A1

WO2023065851A1 - Gas turbine

Info

Publication number: WO2023065851A1
Application number: PCT/CN2022/116640
Authority: WO
Inventors: 靳普
Original assignee: 靳普科技(北京)有限公司
Priority date: 2021-10-19
Filing date: 2022-09-01
Publication date: 2023-04-27
Also published as: CN113898474A

Abstract

A gas turbine, comprising a rotating shaft (10), a gas compressor (20), a combustion chamber (40) and a turbine (30), wherein the gas compressor and the turbine are mounted on the rotating shaft; a gas output end of the gas compressor is in communication with a gas intake end of the combustion chamber; a gas output end of the combustion chamber is in communication with a gas intake end of the turbine; and the combustion chamber is internally provided with a nozzle (70) that is in communication with a fuel storage tank (80). The gas turbine further comprises a supercharger (90) comprising: a shaft (910), and a supercharger gas compressor (920) and a supercharger turbine (930) which are coaxially connected to each other, the gas output end of the gas compressor and/or an exhaust end of the turbine being in communication with a gas intake end of the supercharger turbine, and a gas output end of the supercharger gas compressor being in communication with the nozzle. The supercharger gas compressor supplies high-pressure gas to increase the pressure and speed of fuel injected through the nozzle. The gas output end of the gas compressor is further in communication with the gas intake end of the supercharger gas compressor.

Description

gas turbine

technical field

The invention relates to a gas turbine capable of preventing flame burnback nozzles, and belongs to the technical field of gas turbines.

Background technique

The gas turbine uses continuously flowing gas as the working medium to drive the impeller to rotate at high speed, and converts the energy of the fuel into useful work. It is a rotating impeller heat engine. It mainly includes three major parts: compressor, combustion chamber and turbine: the compressor sucks in air from the external atmosphere and compresses it to pressurize it, and at the same time, the temperature of the air increases accordingly; the compressed air is compressed to the combustion chamber and injected fuel Mixed combustion generates high-temperature and high-pressure gas; then it enters the turbine and expands to do work, pushing the turbine to drive the compressor and the external load rotor to rotate together at high speed, realizing the partial conversion of the chemical energy of the gas or liquid fuel into mechanical work, and can be connected to generate electricity machine output power.

When the combustion chamber is working, the fuel is sprayed and burned through the nozzle to form a flame, and the flame propagation velocity of the fuel and the injection velocity of the fuel determine the position of the formed flame. If the pressure difference is insufficient, it is easy to cause the flame to burn back to the nozzle, especially when the fuel with a lower flame propagation velocity (such as methane) is replaced with a fuel with a higher flame propagation velocity (such as hydrogen), the flame propagation velocity of the fuel increases (such as The flame propagation velocity of hydrogen is about 7 times that of methane), while the injection velocity of the fuel remains the same or the increase is insufficient, so that the position of the flame moves to the nozzle, causing the flame to burn back to the nozzle, so that the nozzle bears a large heat load, It is easy to burn out and block, which will lead to unstable fuel combustion, reduce combustion efficiency, and even cause safety problems in severe cases. In the prior art, the method of strengthening the protection of the nozzle is usually used to protect the nozzle, such as the Chinese invention patent with the publication number CN 106556030 A, which protects the nozzle by setting a thermal protection structure at the nozzle. But such a way can not fundamentally solve the technical problem of the flame back roasting nozzle.

Contents of the invention

Aiming at the above-mentioned prior art, the present invention provides a gas turbine that can prevent the flame from burning back the nozzle. In the present invention, the supercharger is used to pressurize and speed up the fuel ejected from the nozzle, so as to prevent the flame from burning back to the nozzle.

The present invention is achieved through the following technical solutions:

A gas turbine, comprising a rotating shaft, a compressor, a combustion chamber and a turbine, the compressor and the turbine are installed on the rotating shaft, the outlet end of the compressor communicates with the inlet end of the combustion chamber, and the outlet end of the combustion chamber communicates with the inlet end of the turbine , there is a nozzle in the combustion chamber, and the nozzle communicates with the fuel storage tank; it also includes a supercharger, the supercharger includes a shaft, and a coaxially connected supercharger compressor and a supercharger turbine, a supercharger compressor and a supercharger The turbine turbine can rotate synchronously; the outlet end of the compressor and/or the exhaust end of the turbine communicate with the intake end of the turbocharger turbine, the outlet end of the supercharger compressor communicates with the nozzle, and the supercharger compressor provides high-pressure gas , to increase the boost pressure of the fuel sprayed through the nozzle.

Further, the outlet end of the compressor is also in communication with the inlet end of the supercharger compressor.

Preferably, the outlet end of the compressor communicates with the intake end of the combustion chamber and the intake end of the supercharger compressor respectively, and the exhaust end of the turbine communicates with the intake end of the turbocharger turbine. At this time, the intake air of the supercharger compressor comes from the exhaust gas of the compressor, and the power of the turbocharger turbine comes from the exhaust gas of the turbine.

Preferably, the air outlet of the compressor communicates with the intake end of the combustion chamber, the intake end of the supercharger compressor, and the intake end of the turbocharger turbine respectively. At this time, the intake air of the supercharger compressor comes from the exhaust gas of the compressor, and the power of the turbocharger turbine also comes from the exhaust gas of the compressor.

Preferably, the outlet end of the compressor communicates with the intake end of the combustion chamber, the intake end of the supercharger compressor, and the intake end of the supercharger turbine respectively, and the exhaust end of the turbine communicates with the intake end of the supercharger turbine. The intake port is connected. At this time, the intake air of the supercharger compressor comes from the exhaust gas of the compressor, and the power of the turbocharger turbine comes from the exhaust gas of the compressor and the exhaust gas of the turbine.

Preferably, the outlet end of the compressor is only communicated with the intake end of the combustion chamber, and the exhaust end of the turbine is communicated with the intake end of the turbocharger turbine. At this time, the intake air of the supercharger compressor comes from the external environment, and the power of the supercharger turbine comes from the exhaust gas of the turbine.

Preferably, the gas outlet end of the compressor communicates with the intake end of the combustion chamber and the intake end of the turbocharger turbine respectively. At this time, the intake air of the supercharger compressor comes from the external environment, and the power of the supercharger turbine comes from the exhaust gas of the compressor.

Preferably, the outlet end of the compressor communicates with the intake end of the combustion chamber and the intake end of the turbocharger turbine respectively, and the exhaust end of the turbine communicates with the intake end of the turbocharger turbine. At this time, the intake air of the supercharger compressor comes from the external environment, and the power of the supercharger turbine comes from the exhaust gas of the compressor and the exhaust gas of the turbine.

Further, it also includes a free turbine, the free turbine is opposite to the turbine and/or the supercharger turbine, and the exhaust gas of the turbine and/or the supercharger turbine can drive the free turbine to rotate and do work, for example, the free turbine shaft is connected to the generator, so as to Further drive the generator to generate electricity.

Further, the supercharger also includes a motor, which can provide boost for the compressor of the supercharger.

Further, the pressure of the high-pressure gas provided by the supercharger compressor can be flexibly adjusted according to the type of fuel, the pressure of the fuel storage tank and/or the pressure in the combustion chamber, for example, it can be adjusted after changing the fuel (such as hydrogen) (increase) the outlet pressure of the external air source to match.

Further, the pressure of the high-pressure gas fed into the nozzle by the supercharger compressor is greater than the pressure of the gas fed into the combustion chamber by the compressor, which is conducive to keeping the position of the flame away from the nozzle and avoiding the flame back to the nozzle, for example, the pressure difference is greater than 1 atmospheric pressure.

Further, after the fuel injected by the nozzle is pressurized and accelerated, the injection speed is greater than or equal to 20m/s, preferably greater than or equal to 50m/s, more preferably greater than or equal to 340m/s (supersonic speed), the fuel under the supersonic state It is not easy to burn, so that the protection of the nozzle can be formed at the outlet of the nozzle. After the supersonic fuel moves away from the nozzle, the speed drops, and the fuel is ignited again to form a combustion flame.

Further, the front end of the nozzle has a constriction to facilitate the further acceleration of the fuel.

Further, a gas bearing is installed on the rotating shaft, and the gas bearing may be a radial bearing and/or a thrust bearing.

Further, the gas outlet of the supercharger compressor communicates with the gas bearing and supplies gas to the gas bearing.

Further, the gas bearing is a static pressure bearing or a dynamic pressure bearing or a dynamic and static pressure hybrid bearing; when the gas bearing is a static pressure bearing or a dynamic and static pressure hybrid bearing, an external air source connected to the gas bearing is also provided to provide the gas bearing air supply.

In the gas turbine of the present invention, when working, the air intake end of the compressor sucks in air (oxidant) from the external environment and compresses it, and then passes it into the combustion chamber after compression; at the same time, the fuel in the fuel storage tank is ejected through the nozzle, and the compressed air and fuel The mixed combustion spins the turbine and exits through the exhaust port of the turbine. The supercharger compressor supplies air to the nozzle to increase the fuel pressure and speed up through the nozzle, and the fuel is injected into the combustion chamber by the nozzle to burn after the speed up. Due to the increased fuel injection velocity, the position of the flame is moved forward, away from the nozzle, which prevents the flame from burning back into the nozzle. Moreover, the high-pressure gas can reduce the severity of the reaction of the fuel and reduce the emission of nitrogen oxides during the operation of the gas turbine.

In actual application, if the fuel is a fuel with a low flame propagation velocity (such as methane), or there is no flame back-fired nozzle, for the sake of cost saving, the supercharger does not need to supply air to the nozzle. When the fuel is a fuel with a high flame propagation speed (such as hydrogen), or when switching from a fuel with a low flame propagation speed (such as methane) to a fuel with a high flame propagation speed (such as hydrogen), or due to insufficient pressure difference When the flame burns back to the nozzle, the supercharger is controlled to supply air to the nozzle, so that the fuel sprayed out through the nozzle is boosted and accelerated, so that the position of the flame moves forward to keep away from the nozzle, preventing the flame from returning to the nozzle and preventing the nozzle from being burned or clogged.

The gas turbine of the present invention uses a supercharger to pressurize and speed up the fuel sprayed through the nozzle to prevent the flame from back-roasting the nozzle, effectively protect the nozzle, prevent the nozzle from being burned or blocked, and ensure the stability and combustion efficiency of the fuel combustion. The efficiency is not affected, making the operation of the gas turbine stable. The power of the supercharger comes from the compressor or the turbine, which can make full use of the exhaust of the compressor or the exhaust of the turbine, without the need for an external power source, low cost and low energy consumption.

Various terms and phrases used herein have their ordinary meanings known to those skilled in the art. If the terms and phrases mentioned are inconsistent with the known meanings, the meanings expressed in the present invention shall prevail.

Description of drawings

Fig. 1: Schematic diagram of the structure of the gas turbine of Example 1.

Figure 2: Schematic diagram of the nozzle structure.

Figure 3: Schematic diagram of the structure of a nozzle with a constriction.

Fig. 4: Schematic diagram of the structure of the gas turbine of Example 2.

Fig. 5: Schematic diagram of the structure of the gas turbine of Example 3.

Fig. 6: Schematic diagram of the structure of the gas turbine of Embodiment 4.

Fig. 7: Schematic diagram of the structure of the gas turbine of Embodiment 5.

Fig. 8: Schematic diagram of the structure of the gas turbine of Embodiment 6.

Fig. 9: Schematic diagram of the structure of the gas turbine of Example 7.

Fig. 10: Schematic diagram of the structure of the gas turbine of Embodiment 8.

Among them, 10, rotating shaft; 20, compressor; 30, turbine; 40, combustion chamber; 50, external air source; 60, gas bearing; 70, nozzle; 80, fuel storage tank; 90, supercharger; 910, shaft ; 920, turbocharger compressor; 930, turbocharger turbine; IT, intake end of compressor; ET, exhaust end of turbine; FU, fuel; HA, high-pressure gas. The direction indicated by the arrow is the flow direction of gas or fuel.

Detailed ways

The present invention will be further described below in conjunction with embodiment. However, the scope of the present invention is not limited to the following examples. Those skilled in the art can understand that various changes and modifications can be made in the present invention without departing from the spirit and scope of the present invention.

Example 1

A gas turbine, comprising a rotating shaft 10, a compressor 20, a combustion chamber 40 and a turbine 30, the compressor 20 and the turbine 30 are installed on the rotating shaft 10, the gas outlet end of the compressor 20 communicates with the intake end of the combustion chamber 40, and the combustion chamber 40 The outlet end of the combustion chamber communicates with the intake end of the turbine 30, and the combustion chamber 40 is provided with a nozzle 70, and the nozzle 70 communicates with the fuel storage tank 80, as shown in Figure 1; it also includes a supercharger 90, which includes a shaft 910 , and the coaxially connected supercharger compressor 920 and supercharger turbine 930, the supercharger compressor 920 and the supercharger turbine 930 can rotate synchronously; The gas end is communicated, the outlet end of the supercharger compressor 920 is communicated with the nozzle 70, the exhaust end of the turbine 30 is communicated with the intake end of the supercharger turbine 930, and the supercharger compressor 920 provides high-pressure gas HA to pass through the nozzle 70 injected fuel FU supercharging speed.

When the gas turbine with the above structure is in operation, the air inlet IT of the compressor 20 sucks in air (oxidant) from the external environment and compresses it. After compression, a part of it passes into the combustion chamber 40 to mix with the fuel FU ejected through the nozzle 70, and the other part It is passed into the supercharger compressor 920, and after being further compressed by the supercharger compressor 920, it is passed into the nozzle 70 to increase the fuel boost; the fuel FU in the fuel storage tank 80 is injected into the fuel through the nozzle 70 In the combustion chamber 40 , combustion generates high-temperature and high-pressure gas; the high-temperature and high-pressure gas enters the turbine and expands to do work, pushing the turbine to drive the compressor and the external load rotor to rotate together at high speed. As the ejection velocity of the fuel FU increases, the position of the flame moves forward, away from the nozzle 70 , thereby preventing the flame from burning back to the nozzle 70 . After the high-temperature and high-pressure gas does work in the turbine, it is discharged through the exhaust end ET of the turbine 30, and a part of it is passed into the intake end of the turbocharger turbine 930 to drive the turbocharger turbine 930 to rotate, thereby driving the turbocharger compressor 920 Rotate, thereby boosting part of the exhaust gas from the compressor 20.

The supercharger also includes a motor, which can provide boost for the supercharger compressor.

The pressure of the high-pressure gas HA provided by the supercharger compressor 920 can be flexibly adjusted according to the type of fuel, the pressure of the fuel storage tank and/or the pressure in the combustion chamber, for example, it can be adjusted after changing the fuel (such as hydrogen) ( Increase) the outlet pressure of the external air source to match.

The pressure of the high-pressure gas HA that the supercharger compressor 920 passes into the nozzle 70 is greater than the gas pressure that the compressor 20 passes into the combustion chamber 40, which is beneficial to keep the position of the flame away from the nozzle and prevent the flame from returning to the nozzle. The difference is greater than 1 atmosphere.

After the fuel ejected through the nozzle is pressurized and accelerated, the ejection speed is greater than or equal to 340m/s (supersonic speed), and the fuel under the supersonic state is not easy to burn, so that the protection of the nozzle can be formed at the outlet of the nozzle, and the supersonic After the sonic fuel moves away from the nozzle, the velocity decreases, and the fuel is ignited again to form a combustion flame.

The structure of the nozzle 70 is shown in FIG. 2 .

The front end of the nozzle 70 may have a constriction, as shown in FIG. 3 , which is conducive to further fuel acceleration.

Example 2

A gas turbine, comprising a rotating shaft 10, a compressor 20, a combustion chamber 40 and a turbine 30, the compressor 20 and the turbine 30 are installed on the rotating shaft 10, the gas outlet end of the compressor 20 communicates with the intake end of the combustion chamber 40, and the combustion chamber 40 The outlet end of the combustion chamber communicates with the intake end of the turbine 30, and the combustion chamber 40 is provided with a nozzle 70, and the nozzle 70 communicates with the fuel storage tank 80, as shown in Figure 4; it also includes a supercharger 90, which includes a shaft 910 , and coaxially connected supercharger compressor 920 and supercharger turbine 930, supercharger compressor 920 and supercharger turbine 930 can rotate synchronously; The intake end of the supercharger turbine 930 is communicated with the intake end of the supercharger turbine 930, and the outlet end of the supercharger compressor 920 is communicated with the nozzle 70. Boost speed.

The difference with Embodiment 1 is that the air outlet of the compressor 20 communicates with the intake end of the combustion chamber 40, the intake end of the supercharger compressor 920, and the intake end of the supercharger turbine 930 respectively, and the turbine The exhaust port of 30 is not in communication with the intake port of supercharger turbine 930 .

During operation, the intake port IT of the compressor 20 sucks air (oxidant) from the external environment and compresses it. After compression, it is divided into three parts: the first part passes into the combustion chamber 40 and mixes with the fuel FU ejected through the nozzle 70; The second part is passed into the supercharger compressor 920, and after being further compressed by the supercharger compressor 920, it is passed into the nozzle 70 for fuel boosting and speeding up; the third part is passed into the intake end of the supercharger turbine 930 to drive The supercharger turbine 930 rotates, and then drives the supercharger compressor 920 to rotate, thereby supercharging part of the exhaust gas from the compressor 20 . The fuel FU in the fuel storage tank 80 is boosted and accelerated and sprayed into the combustion chamber 40 by the nozzle 70 to burn to generate high-temperature and high-pressure gas; the high-temperature and high-pressure gas enters the turbine and expands to do work, driving the turbine to drive the compressor and the external load rotor Spin together at high speed. As the ejection velocity of the fuel FU increases, the position of the flame moves forward, away from the nozzle 70 , thereby preventing the flame from burning back to the nozzle 70 .

Example 3

A gas turbine, comprising a rotating shaft 10, a compressor 20, a combustion chamber 40 and a turbine 30, the compressor 20 and the turbine 30 are installed on the rotating shaft 10, the gas outlet end of the compressor 20 communicates with the intake end of the combustion chamber 40, and the combustion chamber 40 The outlet end of the combustion chamber communicates with the intake end of the turbine 30, and the combustion chamber 40 is provided with a nozzle 70, and the nozzle 70 communicates with the fuel storage tank 80, as shown in Figure 5; it also includes a supercharger 90, which includes a shaft 910 , and coaxially connected supercharger compressor 920 and supercharger turbine 930, supercharger compressor 920 and supercharger turbine 930 can rotate synchronously; The intake end of the turbocharger turbine 930 is communicated with the intake end of the supercharger turbine 930, the outlet end of the supercharger compressor 920 is communicated with the nozzle 70, the exhaust end of the turbine 30 is communicated with the intake end of the supercharger turbine 930, and the supercharging The compressor compressor 920 supplies high-pressure gas HA to pressurize and speed up the fuel FU sprayed through the nozzle 70 .

The difference from Embodiment 1 is that the outlet end of the compressor 20 is also communicated with the intake end of the turbocharger turbine 930, that is, the power of the turbocharger turbine 930 can come from the exhaust of the compressor 20, Exhaust from the turbine 30 may also be used, or a combination of both.

The difference from Embodiment 2 is that: the exhaust end of the turbine 30 communicates with the intake end of the turbocharger turbine 930 .

During operation, the intake port IT of the compressor 20 sucks air (oxidant) from the external environment and compresses it. After compression, it is divided into three parts: the first part passes into the combustion chamber 40 and mixes with the fuel FU ejected through the nozzle 70; The second part is passed into the supercharger compressor 920, and after being further compressed by the supercharger compressor 920, it is passed into the nozzle 70 for fuel boosting and speeding up; the third part is passed into the intake end of the supercharger turbine 930 to drive The supercharger turbine 930 rotates, and then drives the supercharger compressor 920 to rotate, thereby supercharging part of the exhaust gas from the compressor 20 . The fuel FU in the fuel storage tank 80 is boosted and accelerated and sprayed into the combustion chamber 40 by the nozzle 70 to burn to generate high-temperature and high-pressure gas; the high-temperature and high-pressure gas enters the turbine and expands to do work, driving the turbine to drive the compressor and the external load rotor Spin together at high speed. As the ejection velocity of the fuel FU increases, the position of the flame moves forward, away from the nozzle 70 , thereby preventing the flame from burning back to the nozzle 70 . After the high-temperature and high-pressure gas does work in the turbine, it is discharged through the exhaust end ET of the turbine 30, and a part of it is passed into the intake end of the turbocharger turbine 930 to drive the turbocharger turbine 930 to rotate, thereby driving the turbocharger compressor 920 Rotate, thereby boosting part of the exhaust gas from the compressor 20.

Example 4

A gas turbine, comprising a rotating shaft 10, a compressor 20, a combustion chamber 40 and a turbine 30, the compressor 20 and the turbine 30 are installed on the rotating shaft 10, the gas outlet end of the compressor 20 communicates with the intake end of the combustion chamber 40, and the combustion chamber 40 The outlet end of the combustion chamber communicates with the intake end of the turbine 30, and the combustion chamber 40 is provided with a nozzle 70, and the nozzle 70 communicates with the fuel storage tank 80, as shown in Figure 6; it also includes a supercharger 90, which includes a shaft 910 , and the coaxially connected supercharger compressor 920 and supercharger turbine 930, the supercharger compressor 920 and the supercharger turbine 930 can rotate synchronously; The exhaust end of 30 communicates with the intake end of the supercharger turbine 930 , and the supercharger compressor 920 provides high-pressure gas HA to supercharge and speed up the fuel FU sprayed through the nozzle 70 .

The difference from Embodiment 1 is that the intake air of the supercharger compressor comes from the external environment (that is, the outlet port of the compressor 20 is not in communication with the intake port of the supercharger compressor 920 ).

During operation, the intake port IT of the compressor 20 sucks in air (oxidant) from the external environment and compresses it, and after being compressed, it flows into the combustion chamber 40 and mixes with the fuel FU sprayed out through the nozzle 70 . The supercharger compressor 920 takes in air from the external environment and compresses it, and after the compression, it flows into the nozzle 70 to increase fuel pressure. The fuel FU in the fuel storage tank 80 is boosted and accelerated and sprayed into the combustion chamber 40 by the nozzle 70 to burn to generate high-temperature and high-pressure gas; the high-temperature and high-pressure gas enters the turbine and expands to do work, driving the turbine to drive the compressor and the external load rotor Spin together at high speed. As the ejection velocity of the fuel FU increases, the position of the flame moves forward, away from the nozzle 70 , thereby preventing the flame from burning back to the nozzle 70 . After the high-temperature and high-pressure gas does work in the turbine, it is discharged through the exhaust end ET of the turbine 30, and a part of it is passed into the intake end of the turbocharger turbine 930 to drive the turbocharger turbine 930 to rotate, thereby driving the turbocharger compressor 920 Rotate to compress the air from the external environment.

Example 5

A gas turbine, comprising a rotating shaft 10, a compressor 20, a combustion chamber 40 and a turbine 30, the compressor 20 and the turbine 30 are installed on the rotating shaft 10, the gas outlet end of the compressor 20 communicates with the intake end of the combustion chamber 40, and the combustion chamber 40 The outlet end of the combustion chamber communicates with the intake end of the turbine 30, and the combustion chamber 40 is provided with a nozzle 70, and the nozzle 70 communicates with the fuel storage tank 80, as shown in Figure 7; it also includes a supercharger 90, which includes a shaft 910 , and the coaxially connected supercharger compressor 920 and supercharger turbine 930, the supercharger compressor 920 and the supercharger turbine 930 can rotate synchronously; The gas end is connected, and the outlet end of the supercharger compressor 920 is connected with the nozzle 70 , and the supercharger compressor 920 provides high-pressure gas HA to supercharge and accelerate the fuel FU sprayed through the nozzle 70 .

The difference from Embodiment 2 is that the intake air of the supercharger compressor comes from the external environment (that is, the outlet port of the compressor 20 is not in communication with the intake port of the supercharger compressor 920 ).

During work, the intake port IT of the compressor 20 sucks in air (oxidant) from the external environment and compresses it. After compression, it is divided into two parts: one part passes into the combustion chamber 40 and mixes with the fuel FU ejected through the nozzle 70, and the other part It is connected to the intake end of the supercharger turbine 930, and the supercharger turbine 930 is driven to rotate, and then the supercharger compressor 920 is driven to rotate, thereby compressing the air obtained from the external environment. The supercharger compressor 920 takes in air from the external environment and compresses it, and after the compression, it flows into the nozzle 70 to increase fuel pressure. The fuel FU in the fuel storage tank 80 is boosted and accelerated and sprayed into the combustion chamber 40 by the nozzle 70 to burn to generate high-temperature and high-pressure gas; the high-temperature and high-pressure gas enters the turbine and expands to do work, driving the turbine to drive the compressor and the external load rotor Spin together at high speed. As the ejection velocity of the fuel FU increases, the position of the flame moves forward, away from the nozzle 70 , thereby preventing the flame from burning back to the nozzle 70 .

Example 6

A gas turbine, comprising a rotating shaft 10, a compressor 20, a combustion chamber 40 and a turbine 30, the compressor 20 and the turbine 30 are installed on the rotating shaft 10, the gas outlet end of the compressor 20 communicates with the intake end of the combustion chamber 40, and the combustion chamber 40 The outlet end of the combustion chamber communicates with the intake end of the turbine 30, and the combustion chamber 40 is provided with a nozzle 70, and the nozzle 70 communicates with the fuel storage tank 80, as shown in Figure 8; it also includes a supercharger 90, and the supercharger 90 includes a shaft 910 , and the coaxially connected supercharger compressor 920 and supercharger turbine 930, the supercharger compressor 920 and the supercharger turbine 930 can rotate synchronously; The gas end is communicated, the exhaust end of the turbine 30 is communicated with the intake end of the supercharger turbine 930, the outlet end of the supercharger compressor 920 is communicated with the nozzle 70, and the supercharger compressor 920 provides high-pressure gas HA to pass through the nozzle 70 injected fuel FU supercharging speed up.

The difference from Embodiment 3 is that the intake air of the supercharger compressor comes from the external environment (that is, the outlet end of the compressor 20 is not in communication with the intake end of the supercharger compressor 920 ).

The difference from Embodiment 5 is that: the exhaust end of the turbine 30 communicates with the intake end of the turbocharger turbine 930 . That is: the power of the turbocharger turbine 930 can come from the exhaust of the compressor 20, the exhaust of the turbine 30, or a combination of the two.

During work, the intake port IT of the compressor 20 sucks in air (oxidant) from the external environment and compresses it. After compression, it is divided into two parts: one part passes into the combustion chamber 40 and mixes with the fuel FU ejected through the nozzle 70, and the other part It is connected to the intake end of the supercharger turbine 930, and the supercharger turbine 930 is driven to rotate, and then the supercharger compressor 920 is driven to rotate, thereby compressing the air obtained from the external environment. The supercharger compressor 920 takes in air from the external environment and compresses it, and after the compression, it flows into the nozzle 70 to increase fuel pressure. The fuel FU in the fuel storage tank 80 is boosted and accelerated and sprayed into the combustion chamber 40 by the nozzle 70 to burn to generate high-temperature and high-pressure gas; the high-temperature and high-pressure gas enters the turbine and expands to do work, driving the turbine to drive the compressor and the external load rotor Spin together at high speed. As the ejection velocity of the fuel FU increases, the position of the flame moves forward, away from the nozzle 70 , thereby preventing the flame from burning back to the nozzle 70 . After the high-temperature and high-pressure gas does work in the turbine, it is discharged through the exhaust end ET of the turbine 30, and a part of it is passed into the intake end of the turbocharger turbine 930 to drive the turbocharger turbine 930 to rotate, thereby driving the turbocharger compressor 920 Rotate to compress the air from the external environment.

Example 7

A gas turbine, the structure of which is the same as that of Embodiment 1 (as shown in FIG. 9 ), the difference lies in that: a gas bearing 60 is installed on the rotating shaft 10, and the gas bearing 60 can be a radial bearing and/or a thrust bearing. The position of the gas bearing 60 may be at the end of the rotating shaft 10 away from the turbine 30 , or between the compressor 20 and the turbine 30 , or both.

The gas outlet of the supercharger compressor 920 can communicate with the gas bearing 60 and supply gas to the gas bearing 60 .

The gas bearing 60 may be a hydrostatic bearing or a hydrostatic hybrid bearing, and the gas bearing 60 may communicate with an external gas source 50 .

The external air source 50 may be an air pump.

Example 8

A gas turbine, the structure of which is the same as that of Embodiment 2 (as shown in FIG. 10 ), the difference is that: a gas bearing 60 is installed on the rotating shaft 10, and the gas bearing 60 can be a radial bearing and/or a thrust bearing. The position of the gas bearing 60 may be at the end of the rotating shaft 10 away from the turbine 30 , or between the compressor 20 and the turbine 30 , or both.

The external air source 50 may be an air pump.

Example 9

A kind of gas turbine, the structure is the same as embodiment 1, and difference is: also comprise free turbine, free turbine and turbine and/or supercharger turbine are opposed, and the exhaust of turbine and/or supercharger turbine can drive free turbine to rotate To do work, for example, the free turbine shaft is connected to the generator to further drive the generator to generate electricity.

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

Claims

A gas turbine, comprising a rotating shaft, a compressor, a combustion chamber and a turbine, the compressor and the turbine are installed on the rotating shaft, the outlet end of the compressor communicates with the inlet end of the combustion chamber, and the outlet end of the combustion chamber communicates with the inlet end of the turbine , the combustion chamber is provided with a nozzle, and the nozzle communicates with the fuel storage tank; it is characterized in that: it also includes a supercharger, the supercharger includes a shaft, and a coaxially connected supercharger compressor and a supercharger turbine; the air outlet of the compressor End and/or the exhaust end of the turbine communicates with the intake end of the supercharger turbine, and the outlet end of the supercharger compressor communicates with the nozzle and provides high-pressure gas to boost the fuel sprayed through the nozzle.
The gas turbine according to claim 1, characterized in that: the gas outlet end of the compressor is also in communication with the inlet end of the supercharger compressor.
The gas turbine according to claim 1, further comprising a free turbine, the free turbine is opposite to the turbine and/or the turbocharger turbine, and the exhaust gas of the turbine and/or the supercharger turbine can drive the free turbine to rotate and perform work.
The gas turbine according to claim 1, wherein said supercharger further comprises an electric motor.
The gas turbine according to claim 1, wherein the pressure of the high-pressure gas fed into the nozzle by the supercharger compressor is greater than the pressure of the gas fed into the combustion chamber by the compressor.
The gas turbine according to claim 5, characterized in that the pressure difference between the pressure of the high-pressure gas fed into the nozzle by the supercharger compressor and the pressure of the gas fed into the combustion chamber by the compressor is greater than 1 atmospheric pressure.
The gas turbine according to claim 1, characterized in that, after the fuel injected through the nozzle is boosted and accelerated, the injection velocity of the fuel is greater than or equal to 340m/s.
The gas turbine according to claim 1, wherein the front end of the nozzle has a constriction.
The gas turbine according to claim 1, wherein a gas bearing is installed on the rotating shaft, and the gas bearing is a radial bearing and/or a thrust bearing.
The gas turbine according to claim 9, characterized in that: the gas outlet end of the supercharger compressor communicates with the gas bearing and supplies gas to the gas bearing.