An annular cavity swirling counter-injection structure based on rde combustion chamber

Abstract

The invention provides a ring cavity rotational flow opposite spraying structure based on an RDE combustion chamber. An axial symmetry hook face circular seam is adopted in a circular seam of an RDE,an included angle of the obtuse angle is formed between the transverse jet flow and the main jet flow direction of RDE, single-row annular cavity array cylindrical fuel spraying holes are evenly distributed in the inner and outer wall faces of the head of the RDE combustion chamber, and on the basis of the two-dimensional deflection, circumferential deflection is added on the fuel spraying holes.The structure has the advantages that non-linear circular seam configuration is adopted, pressure losses are reduced, and the outlet flow field is more stable. The upstream area of the transverse jetflow is decelerated, the sufficient fuel penetrating and mixing can be achieved, and the mixing efficiency is improved.

Description

technical field [0001] The invention relates to the technical field of rotary detonation engines, in particular to an annular cavity swirl counter-spray structure based on a large-scale RDE combustion chamber. Background technique [0002] The current aerospace propulsion system is mainly based on isobaric combustion rocket engines, ramjet engines and turbojet engines, etc. This kind of combustion mode often requires additional mechanical components such as booster pumps, compressors, etc. to increase the pressure of the combustible mixture ,complex structure. The detonation combustion mode has the characteristics of self-pressurization, fast combustion rate, and high thermal cycle efficiency, and is especially suitable for high-speed aerospace propulsion systems. Researchers have proposed three detonation engine concepts based on detonation combustion: oblique explosion detonation engines, pulse detonation engines, and rotary detonation engines. These three detonation eng...

AI Technical Summary

Problems solved by technology

[0017] This design structure is proposed based on the cold flow field, without considering the influence of the rotating detonation wave in the combustion chamber

Affected by the mixing effect, the linear expansion slope easily induces the detonation wave to move along the axial direction, which is not conducive to the stability of the detonation wave in the combustion chamber

And the detonation wave moves upstream, which will increase the heating of the wall surface, which is not conducive to thermal protection; image 3 (a) Increasing the angle of the transverse jet does improve the penetration of the fuel, but at the same time the total pressure loss and the mixing effect will decrease

For small-scale RDEs, the limited space and good penetration are sufficient to compensate for the impact of this negative effect, so this scheme is applicable at small scales; the proposed collision jet image 3 (b) and staggered injection image 3 (c), the axes of the fuel injection holes point to the axis of the annulus of the combustion chamber, and the coverage area of ​​a single fuel injection hole is small, so the effect on the improvement of the mixing is limited

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