阅读说明：本技术 一种航空发动机催化点火装置 (Catalytic ignition device of aircraft engine ) 是由 谭俊 郝继红 乔宇 于 2020-11-27 设计创作，主要内容包括：本申请属于发动机点火领域,涉及一种航空发动机催化点火装置,包括：壳体(1),所述壳体(1)包括进气口、出气口以及由进气口及出气口限定的燃气通道,所述进气口连接航空煤油与氧气的混合输出通道,所述出气口连接燃烧室；催化载体(2),设置在壳体(1)的燃气通道内,所述催化载体(2)由金属铂铑制成。本申请的航空发动机催化点火装置可以完成加力燃烧室的点火任务,且产品结构简单,不使用电源,能在发动机内高温环境下长期工作,且具有外场维护和更换方便的优点。(The application belongs to the engine field of igniteing, relates to an aeroengine catalysis ignition, includes: the fuel gas burner comprises a shell (1), wherein the shell (1) comprises a gas inlet, a gas outlet and a fuel gas channel limited by the gas inlet and the gas outlet, the gas inlet is connected with a mixing output channel of aviation kerosene and oxygen, and the gas outlet is connected with a combustion chamber; the catalytic carrier (2) is arranged in a fuel gas channel of the shell (1), and the catalytic carrier (2) is made of metal platinum and rhodium. The catalytic ignition device of the aero-engine can complete the ignition task of the afterburner, is simple in structure, does not use a power supply, can work for a long time in a high-temperature environment in the engine, and has the advantages of convenience in outfield maintenance and replacement.)

1. An aircraft engine catalytic ignition device, comprising:

the fuel gas burner comprises a shell (1), wherein the shell (1) comprises a gas inlet, a gas outlet and a fuel gas channel limited by the gas inlet and the gas outlet, the gas inlet is connected with a mixing output channel of aviation kerosene and oxygen, and the gas outlet is connected with a combustion chamber;

the catalytic carrier (2) is arranged in a fuel gas channel of the shell (1), and the catalytic carrier (2) is made of metal platinum and rhodium.

2. The aircraft engine catalytic ignition device of claim 1, wherein: and a heat insulation plate (3) is arranged between the catalytic carrier (2) and the inner wall of the shell (1).

3. The aircraft engine catalytic ignition device of claim 2, wherein: the heat insulation plate is made of high-temperature resistant ceramic materials.

4. The aircraft engine catalytic ignition device of claim 1, wherein: the catalytic carrier is arranged into a net structure.

5. The aircraft engine catalytic ignition device of claim 1, wherein: the shell (1) is formed by machining high-temperature alloy.

6. The aircraft engine catalytic ignition device of claim 1, wherein: the gas passageway of casing (1) is including admitting air section (11), chemical reaction section (12), exhaust section (13), and section (11) connection admits air the air inlet, exhaust section (13) are connected the gas outlet, chemical reaction section (12) are located between section (11) and the exhaust section (13) of admitting air, and chemical reaction section (12) are provided with baffle (14) in the position department that is close to section (11) of admitting air, baffle (14) are used for guiding the gas in section (11) of admitting air and flow to the inner wall department of chemical reaction section (12), catalytic carrier (2) are fixed in the inner wall department of chemical reaction section (12).

7. The aircraft engine catalytic ignition device of claim 6, wherein:

the inner diameter of the chemical reaction section (12) is larger than the inner diameters of the air inlet section (11) and the air outlet section (13), so that a core part is formed at the inner wall of the chemical reaction section (12), and the catalytic carrier (2) is arranged in the core part.

Technical Field

The application belongs to the field of engine ignition, and particularly relates to a catalytic ignition device for an aircraft engine.

Background

The ignition system used by the afterburner of the aero-engine at present consists of an ignition device, an ignition cable and an ignition electric nozzle, wherein the ignition system is driven by alternating current or direct current power supply provided on the engine, firstly, low-voltage direct current or low-voltage alternating current is converted into high-voltage pulse electric energy by the ignition device, the high-voltage pulse electric energy is transmitted to the ignition electric nozzle through the ignition cable, air at the discharge end of the ignition electric nozzle is punctured, an ignition flower is formed, and therefore fuel oil and air mixed gas in the combustion chamber of the engine is ignited. The ignition system product has the advantages of large ignition energy, controllable energy and higher ignition reliability, but when a fault occurs, the field fault removal and replacement are complex, and the ignition system product is influenced by the use temperature of devices and raw materials, is generally arranged on an engine casing, and only the discharge end of an ignition nozzle is inserted into a combustion chamber of an engine.

Disclosure of Invention

In order to solve the technical problem, the application provides an ignition device which has a simple structure and high temperature resistance and ignites an afterburner in an aircraft engine by a chemical reaction principle so as to meet the specific requirements of the engine.

The application of aeroengine catalytic ignition mainly includes:

the gas inlet is connected with a mixed output channel of aviation kerosene and oxygen, and the gas outlet is connected with a combustion chamber;

and the catalytic carrier is arranged in the gas channel of the shell and is made of metal platinum and rhodium.

Preferably, a heat insulation plate is arranged between the catalytic carrier and the inner wall of the shell.

Preferably, the heat insulation plate is made of a high temperature resistant ceramic-based material.

Preferably, the catalytic carrier is provided as a mesh structure.

Preferably, the housing is formed from a superalloy.

Preferably, the gas passageway of casing is including admitting air section, chemical reaction section, exhaust section, and the section of admitting air is connected the air inlet, the exhaust section is connected the gas outlet, the chemical reaction section is located between the section of admitting air and the exhaust section, and the chemical reaction section is provided with the baffle in the position department of being close to the section of admitting air, the baffle is used for guiding the gas in the section of admitting air to the inner wall department flow of chemical reaction section, catalytic carrier fixes the inner wall department at the chemical reaction section.

Preferably, the inner diameter of the chemical reaction section is larger than the inner diameters of the gas inlet section and the gas outlet section, so that a core portion is formed at the inner wall of the chemical reaction section, and the catalytic carrier is disposed at the core portion.

The catalytic ignition device of the aero-engine can complete the ignition task of the afterburner, is simple in structure, does not use a power supply, can work for a long time in a high-temperature environment in the engine, and has the advantages of convenience in outfield maintenance and replacement.

Drawings

FIG. 1 is a schematic structural diagram of a catalytic ignition device of an aero-engine according to the application.

The device comprises a shell, a catalytic carrier, a thermal baffle, an air inlet section, a chemical reaction section, an exhaust section and a baffle, wherein the shell is 1, the catalytic carrier is 2, the thermal baffle is 3, the air inlet section is 11, the chemical reaction section is 12, the exhaust section is 13, and the baffle is 14.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all embodiments of the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application, and should not be construed as limiting the present application.

Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in this application according to the specific situation.

As shown in fig. 1, the present application provides an aircraft engine catalytic ignition device, comprising essentially:

the device comprises a shell 1, wherein the shell 1 comprises an air inlet, an air outlet and a gas channel limited by the air inlet and the air outlet, the air inlet is connected with a mixing output channel of aviation kerosene and oxygen, and the air outlet is connected with a combustion chamber; and the catalytic carrier 2 is arranged in the gas channel of the shell 1, and the catalytic carrier 2 is made of metal platinum and rhodium.

In some alternative embodiments, a thermal insulation plate 3 is disposed between the catalytic carrier 2 and the inner wall of the housing 1, and the thermal insulation plate may be made of a high temperature resistant ceramic material, or may be made of a thermal insulation material such as foamed plastic, ultra-fine glass wool, high silicon cotton, or vacuum thermal insulation plate.

In some alternative embodiments, the catalytic carrier is provided as a mesh structure, which increases the contact area between the fuel gas and the catalytic carrier, and in alternative embodiments, the mesh structure may be in the form of a protrusion extending from the inner wall of the pipe, the protrusion being made of a platinum-rhodium metal.

In some alternative embodiments, the housing 1 is formed from a superalloy.

The ignition device mainly comprises a product shell, a heat insulating material and a catalytic material. The shell is formed by machining high-temperature alloy, the heat insulation material is made of high-temperature resistant ceramic materials, and the shell and the heat insulation material can be used for a long time in a high-temperature environment in the engine. The catalytic material is processed into a net structure by using metal platinum and rhodium with high catalytic activity so as to increase the contact area of the fuel oil mixed gas and the catalytic material. The catalytic ignition device utilizes the hydrocarbon chemical substances in the aviation kerosene to be mixed with oxygen, and generates violent chemical reaction to generate carbon dioxide and water under the catalysis of a platinum rhodium net at the temperature of 400-500 ℃, and simultaneously generates a large amount of heat, and when the heat causes the ignition point of the aviation kerosene, the fuel oil mixed gas in a combustion chamber is ignited to realize ignition. During the reaction process, the platinum-rhodium alloy is used as a metal catalyst and cannot be lost.

The formula for the catalytic reaction is:

it should be noted that, the air inlet of the catalytic ignition device of the aircraft engine of the present application may further be provided with a valve to control the gas to enter, and in a normal case, the valve is provided in a pre-channel of the catalytic ignition device of the engine of the present application, for example, on a mixed output channel of aviation kerosene and oxygen, it should be understood that the high-temperature fuel mixed gas of the mixed output channel of the present application is compressed to perform work, and itself has a high-temperature condition.

In some optional embodiments, the gas channel of the housing 1 includes an air inlet section 11, a chemical reaction section 12, and an air outlet section 13, the air inlet section 11 is connected to the air inlet, the air outlet section 13 is connected to the air outlet, the chemical reaction section 12 is located between the air inlet section 11 and the air outlet section 13, the chemical reaction section 12 is provided with a baffle 14 at a position close to the air inlet section 11, the baffle 14 is used for guiding the gas in the air inlet section 11 to flow to the inner wall of the chemical reaction section 12, and the catalytic carrier 2 is fixed at the inner wall of the chemical reaction section 12.

Referring to fig. 1, in view of the fixation of the catalytic carriers, the catalytic carriers are disposed on the heat insulation plate 3 close to the inner wall of the housing, and a part of the catalytic carriers are disposed on the baffle plate 14, and the baffle plate 14 is also made of heat insulation material, and may be designed separately from the heat insulation plate 3 or may be integrally formed with the heat insulation plate 3.

In some alternative embodiments, the inner diameter of the chemical reaction section 12 is larger than the inner diameters of the gas inlet section 11 and the gas outlet section 13, so that a core portion is formed at the inner wall of the chemical reaction section 12, and the catalytic carrier 2 is disposed in the core portion.

It can be understood that the inner diameter of the chemical reaction section 12 is made large, so that the high-temperature fuel mixed gas can flow along the flow direction shown in fig. 1, i.e. the high-temperature fuel mixed gas expands and contracts first, and the ignition effect is better.

The catalytic ignition device of the aero-engine can complete the ignition task of the afterburner, is simple in structure, does not use a power supply, can work for a long time in a high-temperature environment in the engine, and has the advantages of convenience in outfield maintenance and replacement.

Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.