CN220689129U

CN220689129U - Device for judging knocking combustion chamber explosion

Info

Publication number: CN220689129U
Application number: CN202322388449.7U
Authority: CN
Inventors: 于宁; 韦焕程; 曹新巧; 王琳; 杨占生; 唐泽涵
Original assignee: Qinghang Aerospace Beijing Technology Co ltd
Current assignee: Qinghang Aerospace Beijing Technology Co ltd
Priority date: 2023-09-04
Filing date: 2023-09-04
Publication date: 2024-03-29
Anticipated expiration: 2033-09-04

Abstract

The application provides a device for judging explosion of a detonation combustor, which belongs to the technical field of gas turbines and comprises a pre-detonation tube arranged on the detonation combustor and a high-frequency pressure sensor for collecting pressure in the detonation combustor; the high-frequency pressure sensor is connected with the control system, the pre-explosion tube is provided with a hollow structure, one end of the pre-explosion tube is connected with the detonation combustion chamber, the hollow structure is communicated with the fluid circulation space of the detonation combustion chamber, the other end of the pre-explosion tube is provided with an ignition member, a pre-explosion tube fuel inlet and a pre-explosion tube oxidant inlet which are not communicated with each other are arranged on the pre-explosion tube near the ignition member, and an excitation step is arranged on the inner wall of the pre-explosion tube. By the processing scheme, the explosion of the knocking combustion chamber can be effectively identified, and the problems of low combustion efficiency, low output power and high slow combustion emission caused by slow combustion after explosion are solved.

Description

Device for judging knocking combustion chamber explosion

Technical Field

The application relates to the technical field of gas turbines, in particular to a device for judging knocking combustion chamber explosion.

Background

A gas turbine is a mechanical device for generating power by using gas energy. It is generally composed of three parts: gas engines, generators and auxiliary equipment. In a gas engine, gas is compressed, mixed with air, and burned at a high temperature. The high temperature gas generated by combustion flows through the piston to enable the piston to move up and down, thereby driving the rotor to rotate. The rotor is provided with a generator, and the generator can rotate when the rotor rotates to generate electric energy. Auxiliary equipment includes cooling systems, oil systems, exhaust systems, etc., which function to assist the gas engine in proper operation. For example, the cooling system may maintain the temperature of the gas engine within a suitable range; the oil circuit system can provide lubricating oil for the gas engine; the exhaust system may then exhaust the exhaust gas produced by the gas engine.

Detonation combustion (detonation combustion) is a combustion technique that achieves combustion by propagation of detonation waves. Detonation waves are shock waves that propagate in a detonation reaction, enabling the reactants and oxygen to react rapidly after contact. Detonation combustion techniques may be used to increase combustion efficiency, reduce pollution, and operate at higher pressures and temperatures. Detonation combustion technology is currently used in the automotive, aerospace and aerospace fields.

Rotary detonation combustion (rotating detonation combustion) is a combustion technique that achieves combustion by rotating detonation waves. Detonation waves are shock waves that propagate in a detonation reaction, enabling the reactants and oxygen to react rapidly after contact. Rotary detonation combustion is a relatively new technology that is currently used in the automotive, aerospace and aerospace fields, primarily for improving combustion efficiency and reducing pollution.

A combustion chamber: the combustion chamber of the gas turbine mixes and combusts fuel and air therein to generate high-temperature and high-pressure gas to drive the rotary member. The design and performance of the combustor has a significant impact on the efficiency, power output and emission levels of the gas turbine.

The parallel detonation gas turbine is internally provided with a conventional combustion chamber and a detonation combustion chamber, when the detonation combustion chamber actually works, the detonation combustion chamber is in a detonation state, but the combustion process is still continuous, but the combustion at the moment is slow combustion, the slow combustion has slower combustion speed and longer flame length, so that a downstream pipeline and the detonation turbine are easily damaged, and the slow combustion has the problems of low combustion efficiency, low output power and high slow combustion emission. Therefore, it is important to accurately judge whether the knocking combustion chamber is in explosion or not, however, the traditional combustion chamber monitoring means such as exhaust temperature, flame detection and the like cannot effectively judge whether the knocking combustion chamber is in explosion or not.

Disclosure of Invention

In view of this, the embodiment of the application provides a device for judging the explosion of a detonation combustion chamber, which at least partially solves the problem that whether the detonation combustion chamber is exploded or not can not be effectively judged in the prior art.

The embodiment of the application provides a device for judging explosion of a detonation combustor, wherein the detonation combustor is fixed on a gas turbine and comprises a pre-detonation tube arranged on the detonation combustor and a high-frequency pressure sensor for collecting pressure in the detonation combustor; the high-frequency pressure sensor is connected with the control system, the pre-explosion tube is provided with a hollow structure, one end of the pre-explosion tube is connected with the detonation combustion chamber, the hollow structure is communicated with a fluid circulation space of the detonation combustion chamber, the other end of the pre-explosion tube is provided with an ignition member, a pre-explosion tube fuel inlet and a pre-explosion tube oxidant inlet which are not communicated with each other are arranged on the pre-explosion tube at positions close to the ignition member, and an excitation step is arranged on the inner wall of the pre-explosion tube.

According to a specific implementation manner of the embodiment of the application, the pre-explosion tube fuel inlet and the pre-explosion tube oxidant inlet are oppositely arranged on the pre-explosion tube.

According to a specific implementation manner of the embodiment of the application, the excitation step is arranged below the pre-explosion tube fuel inlet and the pre-explosion tube oxidant inlet.

According to a specific implementation manner of the embodiment of the application, the excitation step is arranged in a circumferential annular manner along the inner wall of the pre-explosion tube, and the excitation step is arranged into a step structure protruding towards the central axis of the pre-explosion tube along the inner wall of the pre-explosion tube.

According to a specific implementation manner of the embodiment of the application, the excitation steps are uniformly arranged in a plurality of directions along the length direction of the pre-detonation tube.

According to a specific implementation manner of the embodiment of the application, the high-frequency pressure sensor is arranged at one end of the pre-explosion tube, which is close to the detonation combustion chamber, and the measuring head of the high-frequency pressure sensor is communicated with the fluid circulation space of the detonation combustion chamber through the hollow structure of the pre-explosion tube.

According to a specific implementation manner of the embodiment of the application, the high-frequency pressure sensor is arranged on the detonation combustion chamber, and a measuring head of the high-frequency pressure sensor is positioned in a fluid circulation space of the detonation combustion chamber.

According to a specific implementation of an embodiment of the present application, the ignition member is provided as a spark plug.

According to a specific implementation of an embodiment of the present application, the detonation combustor is connected to the gas turbine using a rigid member.

Advantageous effects

The device for judging the explosion of the detonation combustion chamber in the embodiment of the application can more effectively judge whether the combustion chamber is exploded or not by utilizing pressure fluctuation generated by continuous rotary detonation combustion through arranging the pre-detonation tube with an excitation step and the high-frequency pressure sensor, so that the problems of low combustion efficiency, reduced output power and high slow combustion emission caused by slow combustion after explosion are solved.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a block diagram of an apparatus for determining a detonation of a detonation combustor in accordance with an embodiment of the present utility model;

fig. 2 is a block diagram of a pre-detonation tube in accordance with an embodiment of the present utility model.

In the figure: 1. a detonation combustion chamber; 2. pre-bursting tube; 21. a pre-detonation tube fuel inlet; 22. pre-detonation tube oxidant inlet; 23. exciting the step; 24. a spark plug; 3. a high frequency pressure sensor; 4. a rigid member.

Detailed Description

Embodiments of the present application are described in detail below with reference to the accompanying drawings.

Other advantages and effects of the present application will become apparent to those skilled in the art from the present disclosure, when the following description of the embodiments is taken in conjunction with the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, of the embodiments of the present application. The present application may be embodied or carried out in other specific embodiments, and the details of the present application may be modified or changed from various points of view and applications without departing from the spirit of the present application. It should be noted that the following embodiments and features in the embodiments may be combined with each other without conflict. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.

It is noted that various aspects of the embodiments are described below within the scope of the following claims. It should be apparent that the aspects described herein may be embodied in a wide variety of forms and that any specific structure and/or function described herein is merely illustrative. Based on the present application, one skilled in the art will appreciate that one aspect described herein may be implemented independently of any other aspect, and that two or more of these aspects may be combined in various ways. For example, an apparatus may be implemented and/or a method practiced using any number of the aspects set forth herein. In addition, such apparatus may be implemented and/or such methods practiced using other structure and/or functionality in addition to one or more of the aspects set forth herein.

It should also be noted that the illustrations provided in the following embodiments merely illustrate the basic concepts of the application by way of illustration, and only the components related to the application are shown in the drawings and are not drawn according to the number, shape and size of the components in actual implementation, and the form, number and proportion of the components in actual implementation may be arbitrarily changed, and the layout of the components may be more complicated.

In addition, in the following description, specific details are provided in order to provide a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects may be practiced without these specific details.

Currently, the combustion chamber of a gas turbine is generally composed of a combustion chamber body, a burner, a fuel nozzle, a combustion air supply line, an igniter, and the like. The combustion chamber body is a closed container, and the combustor and the fuel nozzle are arranged in the combustion chamber body. The burner is a component for mixing fuel and air and igniting the fuel, and has various structures and forms, such as disk, ring, spray, etc. The fuel nozzles are components that inject fuel into the combustor, and the number, location, and layout of such parameters can also affect the performance of the combustion chamber.

During operation of the gas turbine, fuel and air are mixed through a fuel nozzle and a combustor and ignited to generate high-temperature and high-pressure fuel gas, which is expanded and accelerated in a combustion chamber and then converted into kinetic energy through a rotating member, thereby driving a generator or other equipment. Meanwhile, the design of gas turbine combustors also requires consideration of emissions reduction and combustion efficiency improvement.

The parallel detonation gas turbine has a conventional combustion chamber and a detonation combustion chamber, and the detonation of the detonation combustion chamber can cause the problems of low combustion efficiency, low output power and high slow combustion emission.

In order to solve the above problems, an embodiment of the present application provides a device for judging detonation of a detonation combustor, with specific structure referring to fig. 1 and 2, the detonation combustor 1 is fixed on a gas turbine, and the device includes a pre-detonation tube 2 arranged on the detonation combustor 1 and a high-frequency pressure sensor 3 for collecting pressure in the detonation combustor 1; the high-frequency pressure sensor 3 is connected with the control system, the pre-explosion tube 2 is provided with a hollow structure, one end of the pre-explosion tube 2 is connected with the detonation combustion chamber 1, the hollow structure is communicated with the fluid circulation space of the detonation combustion chamber 1, the other end of the pre-explosion tube 2 is provided with an ignition member, a pre-explosion tube fuel inlet 21 and a pre-explosion tube oxidant inlet 22 which are not communicated with each other are arranged on the pre-explosion tube 2 at positions close to the ignition member, and an excitation step 23 is arranged on the inner wall of the pre-explosion tube 2.

In order to fully mix the fuel and the oxidant for blasting, a pre-detonation tube fuel inlet 21 and a pre-detonation tube oxidant inlet 22 are arranged on the pre-detonation tube 2 in an opposite manner. Specifically, the longitudinal direction of the pre-detonation tube 2 is perpendicular to the detonation combustion chamber 1, the ignition member is located at the top end of the pre-detonation tube 2, and the pre-detonation tube fuel inlet 21 and the pre-detonation tube oxidant inlet 22 are disposed below the ignition member and are located on both sides in the width direction of the pre-detonation tube 2, respectively.

Preferably, the excitation step 23 is arranged below the pre-detonation tube fuel inlet 21 and the pre-detonation tube oxidant inlet 22, the excitation step 23 is arranged in a circumferential annular manner along the inner wall of the pre-detonation tube 2, the excitation step 23 is arranged in a step structure protruding towards the central axis of the pre-detonation tube 2 along the inner wall of the pre-detonation tube 2, and a plurality of excitation steps 23 are uniformly arranged along the length direction of the pre-detonation tube 2.

The principle of exciting the step 23 is: the flame combustion propagation speed is slower under the laminar flow state, turbulence can be formed after the steps are added, the flame can be accelerated under the turbulence, and pulse detonation can be formed by accelerating a plurality of steps for continuous rotary detonation ignition.

In particular, the step may be in the form of a machined annular step or the excitation step 23 of the inner wall of the pre-detonation tube 2 may be replaced by a section of spring.

Further, the high-frequency pressure sensor 3 is for measuring the pressure in the knocking combustion chamber 1, and therefore, the measurement head of the high-frequency pressure sensor 3 can meet the setting requirement as long as it is in contact with the fluid in the combustion chamber. Accordingly, the high-frequency pressure sensor 3 may be provided in one of the following two ways. One is that the high-frequency pressure sensor 3 is arranged at one end of the pre-detonation tube 2 close to the detonation combustion chamber 1, and the measuring head of the high-frequency pressure sensor 3 is communicated with the fluid circulation space of the detonation combustion chamber 1 through the hollow structure of the pre-detonation tube 2; the other is that a high-frequency pressure sensor 3 is arranged on the detonation combustion chamber 1, and a measuring head of the high-frequency pressure sensor 3 is positioned in a fluid circulation space of the detonation combustion chamber 1. In practical application, the adjustment can be performed according to specific application conditions.

In one embodiment, the ignition means is provided as a spark plug 24, with the fuel and the oxidant being ignited by the spark plug 24, the flame forming a continuously rotating knocking ignition under the influence of the excitation step 23.

In practice, detonation combustor 1 is connected to a gas turbine using a rigid member 4.

In the specific implementation, the connection mode of the pre-detonation tube 2 and the detonation combustion chamber 1 can be threaded connection, the detonation combustion chamber 1 is provided with a threaded hole, the pre-detonation tube 2 is in threaded connection with the threaded hole on the detonation combustion chamber 1 through the threads on the pre-detonation tube 2, in the specific implementation, the pre-detonation tube 2 can be fixedly connected to the detonation combustion chamber 1 through a flange or other mechanical connection modes, the connection mode of the pre-detonation tube 2 and the detonation combustion chamber 1 is not particularly limited, and the implementation is carried out according to the fixed connection of the pre-detonation tube 2 and the detonation combustion chamber 1.

Working principle of the device for judging detonation of detonation combustor 1 in the application: the high-frequency pressure sensor 3 collects pressure signals in real time and transmits the pressure signals to the control system, the control system analyzes the interval time t of two adjacent high-frequency pulsation signals (pressure signals), the flame propagation speed is calculated, and the calculation formula of the flame propagation speed is as follows: flame propagation speed = detonation combustor perimeter/interval time t, when flame propagation speed is lower than detonation combustion flame speed threshold value, the detonation combustor 1 can be judged to be in explosion, after the control system judges to be in explosion, an instruction is sent to the pre-detonation tube 2, the pre-detonation tube 2 is connected with pre-detonation tube fuel and pre-detonation tube oxidant, the pre-detonation tube is ignited through the spark plug 24, high-energy pulse waves are formed under the action of the excitation step 23, and continuous rotary detonation in the detonation combustor 1 is excited again.

It should be noted that, the theoretical speed of detonation combustion is related to fuel, temperature, pressure, etc., and is generally greater than 1000m/s, and the threshold value of the flame speed of detonation combustion may be set lower, such as about 300m/s, so as to avoid misjudgment of the device.

The device for judging detonation of the detonation combustion chamber improves the precision of judging detonation of the detonation combustion chamber of the parallel detonation gas turbine by arranging the pre-detonation tube 2 with the excitation step 23 and the high-frequency pressure sensor 3, so that the problems of low combustion efficiency, low output power loss and high slow combustion emission caused by slow combustion after detonation are solved.

The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. The device for judging the explosion of the detonation combustor is characterized in that the device comprises a pre-explosion tube (2) arranged on the detonation combustor (1) and a high-frequency pressure sensor (3) for collecting the pressure in the detonation combustor (1); the high-frequency pressure sensor (3) is connected with the control system, the pre-explosion tube (2) is provided with a hollow structure, one end of the pre-explosion tube (2) is connected with the detonation combustion chamber (1), the hollow structure is communicated with a fluid circulation space of the detonation combustion chamber (1), the other end of the pre-explosion tube (2) is provided with an ignition member, a pre-explosion tube fuel inlet (21) and a pre-explosion tube oxidant inlet (22) which are not communicated with each other are arranged on the pre-explosion tube (2) at positions close to the ignition member, and an excitation step (23) is arranged on the inner wall of the pre-explosion tube (2).

2. The device for judging the explosion of a detonation combustor according to claim 1, wherein the pre-detonation tube fuel inlet (21) and the pre-detonation tube oxidant inlet (22) are oppositely arranged on the pre-detonation tube (2).

3. The device for judging the detonation of the detonation combustor according to claim 1, wherein the excitation step (23) is arranged below the pre-detonation tube fuel inlet (21) and the pre-detonation tube oxidant inlet (22).

4. The device for judging knocking combustion chamber explosion according to claim 1, wherein the excitation step (23) is arranged in a circumferential ring along the inner wall of the pre-explosion tube (2), and the excitation step (23) is arranged in a step structure protruding toward the central axis of the pre-explosion tube (2) along the inner wall of the pre-explosion tube (2).

5. The device for judging knocking combustion chamber explosion according to claim 4, wherein the exciting steps (23) are uniformly provided in plurality along the length direction of the pre-explosion tube (2).

6. The device for judging the detonation of the detonation combustion chamber according to claim 1, wherein the high-frequency pressure sensor (3) is arranged at one end of the pre-detonation tube (2) close to the detonation combustion chamber (1), and the measuring head of the high-frequency pressure sensor (3) is communicated with the fluid circulation space of the detonation combustion chamber (1) through the hollow structure of the pre-detonation tube (2).

7. The device for judging knocking combustion chamber explosion according to claim 1, wherein the high-frequency pressure sensor (3) is provided on the knocking combustion chamber (1), and a measurement head of the high-frequency pressure sensor (3) is located in a fluid circulation space of the knocking combustion chamber (1).

8. Device for determining the detonation of a detonation combustion chamber according to any of the claims 1-7, characterized in that the ignition means is provided as a spark plug (24).

9. Device for determining the detonation of a detonation combustor according to any of the claims 1-7, characterized in that the detonation combustor (1) is connected to the gas turbine by means of a rigid element (4).