CN111520766A

CN111520766A - Radial grading detonation afterburner

Info

Publication number: CN111520766A
Application number: CN202010186199.7A
Authority: CN
Inventors: 张群; 李程镐; 刘强; 杨福正; 曹婷婷; 程祥旺; 李小龙; 胡凡
Original assignee: Northwestern Polytechnical University
Current assignee: Northwestern Polytechnical University
Priority date: 2020-03-17
Filing date: 2020-03-17
Publication date: 2020-08-11

Abstract

The invention discloses a radial graded detonation afterburner. The afterburner is composed of an afterburner inner cone, an afterburner main combustion area, an afterburner inner wall surface, a detonation ring cavity and an afterburner outer wall surface from inside to outside in the radial direction. The head of the detonation ring cavity is provided with a flame linking ring cavity which is connected with the air inlet channel and a main combustion area in the afterburner. The radial grading detonation afterburner can work in a state that a detonation ring cavity does not operate, when the detonation ring cavity needs to be further accelerated, a fuel nozzle injects fuel, flame in the afterburner enters a crossfire ring cavity to realize ignition, and detonation is realized in the detonation ring cavity, so that the aircraft is further accelerated. The pulse detonation combustor has the advantages of simple structure, high cycle heat efficiency and low oil consumption, and the integrated radial grading design ensures that the pulse detonation combustor can realize more efficient and high-speed flight under the condition of not obviously increasing energy consumption and structural complexity.

Description

Radial grading detonation afterburner

Technical Field

The invention belongs to the field of aero-engines, and particularly relates to a radial staged detonation afterburner.

Background

In order to improve the operational performance of the aircraft and enlarge the envelope of the aircraft, the power device of the military fighter increases the thrust by afterburning, and the afterburner is an important technical means for improving the thrust-weight ratio of the aircraft engine. The afterburner is a device for injecting oil to ignite and burn in the gas behind the turbine or the mixture of the gas and the outer culvert so as to improve the temperature of airflow and increase the thrust of the engine in a short time. The development process of the afterburner is a process of continuously improving afterburning temperature, combustion efficiency and combustion stability, reducing fluid loss, reducing weight and improving reliability and applicability. The development of advanced fighter aircraft puts higher requirements on the performance of aircraft engines, and the design of afterburners faces a series of challenges.

The Pulse Detonation Engine (PDE for short) is a new concept Engine which utilizes high-temperature and high-pressure fuel gas generated by intermittent Detonation waves to generate thrust, and the cycle process can be divided into 1, wherein a fuel oxidant fills a Detonation chamber; 2. igniting and detonating; 3. the detonation wave propagates to the open end; 4. the detonation wave reaches the outlet, the expansion wave is reflected back, and the detonation product is discharged from the detonation chamber; 5. the outlet state is restored. The above processes are carried out circularly, and approximately continuous propelling power can be provided for the aircraft after the knocking reaches a certain frequency. Pulse detonation engines offer a number of advantages over conventional engines, of which the simplicity of construction and high cycle thermal efficiency are particularly important. The structure is simple, the engine has small size, light weight and simple maintenance; the circulating heat efficiency is high, the aircraft can fly at the number of M of 0-10 and the flying height of 0-50 km, and the thrust is adjustable; the engine has wide application range, can work in a self-air-suction mode or a rocket engine mode carrying an oxidant, and can also be combined with a ramjet engine or a turbofan engine to form a combined cycle engine or a hybrid engine. In addition, the pulse detonation engine also shows good economy, the rapid reaction mode of detonation combustion enables the whole combustion process to be approximately isovolumetric combustion, the fuel efficiency is improved, the high temperature of detonation also enables incompletely combusted fuel to be greatly reduced, and the factors are beneficial to improving the economy.

In summary, the advantages of pulse detonation engine such as simple structure and high thermal efficiency can be fully used to improve the performance of the current afterburner, and it is necessary to conduct research on the relevant aspects, and reasonably use the pulse detonation combustion technology in the afterburner to find a more optimized design.

Disclosure of Invention

The invention aims to solve the technical problem of providing a radial graded detonation afterburner, which further has the functions of improving the operational performance of an airplane and enlarging the envelope of the airplane, and simultaneously improves the afterburner afterburning temperature, the combustion efficiency, the reliability and the applicability.

Technical scheme

The invention aims to provide a radial staged detonation afterburner.

The technical scheme of the invention is as follows:

the utility model provides a radial hierarchical detonation afterburner, includes the structure and the arrangement of detonation ring chamber, the mounted position and the structure of the flame ring chamber that the detonation ring chamber head is connected, intake duct structure, the structure that flame ring chamber and afterburner owner fire zone link to each other and afterburner internal face's profile design.

The radial staged detonation afterburner is characterized in that: the detonation ring cavity is arranged between the inner wall and the outer wall of the afterburner and is of an annular channel structure, the detonation ring cavity and the wall surface of the afterburner are integrally designed, the wall surface of the detonation ring cavity adopts a spiral structure or a structure with built-in threads, bosses and the like to reduce the DDT distance and further reduce the axial length of the whole combustor according to actual conditions, and the internal structure of the detonation ring cavity is not limited.

The radial staged detonation afterburner is characterized in that: the upstream of the crossfire ring cavity of the head part is connected with an air inlet channel of an annular structure, an openable annular ignition channel is arranged at the position close to the inner wall of the afterburner and is connected with a main combustion area of the afterburner, fuel nozzles are uniformly arranged along the circumferential direction, and the crossfire ring cavity is also positioned between the inner wall and the outer wall of the afterburner.

The radial staged detonation afterburner is characterized in that: the inner wall surface inlet of the afterburner has a streamline contraction structure, the rear half part of the afterburner is of a linear structure and is attached to the crossfire ring cavity and the detonation ring cavity to the maximum extent, so that an annular ignition channel on the crossfire ring cavity can be directly connected with the flame and the crossfire ring cavity of the main combustion area of the afterburner.

The invention has the following beneficial effects:

the radial graded detonation afterburner disclosed by the invention adopts a radial graded arrangement structure, and a detonation ring cavity and other structures are arranged between the inner wall surface and the outer wall surface of the traditional afterburner. In addition, the integral design that the structures such as the detonation ring cavity are positioned between the inner wall surface and the outer wall surface of the afterburner and the joint streamline design of the inner wall surface also ensure the smoothness of an internal airflow channel of the afterburner to the greatest extent, reduce the flow loss and increase the compactness of the structure.

Drawings

FIG. 1: overall structure schematic diagram of radial staged detonation afterburner

FIG. 2: sectional view of radial staged detonation afterburner

In the figure: 1. a boosting inner cone 2, a rectifying support plate 3, an air inlet channel 4, a fuel nozzle 5 and an annular ignition channel,

6. a cross-flame ring cavity 7, a detonation ring cavity 8, an inner wall surface of an afterburner 9 and an outer wall surface of the afterburner

Detailed Description

The invention will now be further described with reference to the accompanying drawings in which:

with reference to fig. 1 and 2, the invention provides a radial staged detonation afterburner. Fig. 1 is a schematic view of the overall structure of a radial staged detonation afterburner, and fig. 2 is a sectional view of the radial staged detonation afterburner.

When the detonation ring cavity is required to operate and a further accelerated aircraft is required, the annular ignition channel (5) is opened, flame in a main combustion area of the afterburner continuously flows into the crossfire ring cavity (6), mixed gas after the main combustion area flows into the crossfire ring cavity (6) through the air inlet channel (3) to be mixed with fuel oil sprayed from the fuel nozzle (4), and then the mixed gas is ignited by the flame entering from the annular ignition channel (5). The ignited mixture and the compression wave enter the detonation ring cavity (7) and are detonated in the detonation ring cavity, and products are directly discharged through the tail of the detonation ring cavity (7) to generate thrust. In addition, when the structures such as the detonation ring cavity and the like work, the combustion and working processes in the afterburner continuously work as the traditional afterburner. According to the pulse detonation engine, the detonation ring cavity and other structures are arranged between the inner wall surface and the outer wall surface of the traditional afterburner, the defects that the afterburning temperature of the current afterburner needs to be improved, the combustion efficiency is low and the like are overcome by utilizing the characteristics of simple structure, high circulating heat efficiency, low oil consumption and the like of the pulse detonation engine, the operational performance of an airplane is further improved, the envelope of the airplane is enlarged, and the afterburning temperature, the combustion efficiency, the reliability and the applicability of the afterburner are improved. The integral design that the structures such as the detonation ring cavity are positioned between the inner wall surface and the outer wall surface of the afterburner and the joint streamline design of the inner wall surface also ensure the smoothness of an internal airflow channel of the afterburner to the greatest extent, reduce the flow loss and increase the compactness of the structure.

Claims

1. The utility model provides a radial hierarchical detonation afterburner, includes the structure and the arrangement of detonation ring chamber, the mounted position and the structure of the flame ring chamber that the detonation ring chamber head is connected, intake duct structure, the structure that flame ring chamber and afterburner owner fire zone link to each other and afterburner internal face's profile design.

2. A radially staged detonation afterburner as claimed in claim 1, wherein: the detonation ring cavity is arranged between the inner wall and the outer wall of the afterburner and is of a ring channel structure, the smoothness of an internal airflow channel of the afterburner is guaranteed to the greatest extent by the integrated design of the detonation ring cavity and the wall surface of the afterburner, the flow loss is reduced, the wall surface of the detonation ring cavity adopts a spiral structure or a built-in thread, a boss and other structures to reduce the DDT distance and further reduce the axial length of the whole combustor according to actual conditions, and the internal structure of the detonation ring cavity is not limited.

3. A radially staged detonation afterburner as claimed in claim 1, wherein: the upstream of the crossfire ring cavity of the head is connected with an air inlet channel of an annular structure, an openable annular ignition channel is arranged on the position close to the inner wall of the afterburner and connected with a main combustion area of the afterburner, and fuel nozzles are uniformly arranged along the circumferential direction, and the crossfire ring cavity is also arranged between the inner wall and the outer wall of the afterburner, so that the integrity of an airflow flow path in the afterburner is ensured, the flow resistance loss is reduced, and the structure compactness is improved.

4. A radially staged detonation afterburner as claimed in claim 1, wherein: the inlet of the inner wall surface of the afterburner has a streamline contraction structure, the rear half part of the afterburner is of a linear structure and is attached to the crossfire annular cavity and the detonation annular cavity to the maximum extent, so that an annular ignition channel on the crossfire annular cavity can be directly connected with the flame and the crossfire annular cavity in the main combustion area of the afterburner, the internal circulation area is increased, the flow resistance in the afterburner is reduced, and the structural compactness is increased.