Single concave cavity trapped vortex combustor

A combustor and cavity technology, applied in the field of new concept aviation gas turbine combustion, can solve the problems of stability and combustion efficiency limitation of trapped vortex combustor, complex fuel system, etc., to improve combustion efficiency and ignition performance, simple fuel system, The effect of reducing the weight of the combustion chamber
CN103277811BInactive Publication Date: 2015-10-28NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Patent Information

Authority / Receiving Office
CN Β· China
Patent Type
Patents(China)
Current Assignee / Owner
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
Publication Date
2015-10-28
Estimated Expiration
Not applicable Β· inactive patent

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Abstract

A single-cavity trapped vortex combustor comprises a pressure expander, an inner cartridge receiver, an outer cartridge receiver, a flame tube, a flow guide device, a pre-evaporation device, an oil supply system and a high-energy spark plug, wherein airflow at an inlet of the combustor enters the combustor through the pressure expander, the flame tube is of a single-cavity structure, the inner cartridge receiver, the outer cartridge receiver and the flame tube form an inner duct and an outer duct of the combustor, the flow guide device separates the main flow from the air of the outer duct, air is decelerated and pressurized through the pressure expander, is divided into four paths through the flow guide device and the pre-evaporation device, and respectively enters the main flow, the pre-evaporation device, the inner duct and the outer duct, and the high-energy spark plug is arranged at the bottom of the cavity. The combustion area of the single-cavity trapped vortex combustor is divided into a trapped vortex area and a main combustion area, and the single-cavity trapped vortex combustor further comprises a flame joint supporting plate which transmits flames from a cavity to the main flow.
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Description

Technical field:

[0001] The invention relates to a single-cavity vortex combustion chamber, which is mainly used as the main combustion chamber of an aero-engine, and belongs to the technical field of new-concept aero-gas turbine combustion. Background technique:

[0002] With the further development of aero-engine technology, the thrust-to-weight ratio continues to increase, the inlet temperature of the combustion chamber increases, the oil-gas ratio and temperature rise of the combustion chamber increase, and the requirements for the performance of the combustion chamber gradually increase, but at the same time, the weight of the combustion chamber is limited. Further increase, therefore, the development of the high-fuel ratio combustion chamber is facing many technical challenges: 1. Stable operation in a wider range, mainly to solve the combustion stability under low power state and the invisible exhaust leakage under high power state; Smoke combustion; 2. Under the cond...

Claims

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