Pneumatic auxiliary type cavity support plate flame stabilizer
A flame stabilizer and pneumatically assisted technology, applied in the combustion method, combustion chamber, combustion equipment and other directions, can solve the problem of deteriorating the ignition performance and flame stability ability of the combustion chamber on duty, destroying the flow pattern in the duty area, and increasing the flow speed of the flame stabilizer on duty. and other problems, to achieve the effect of improving ignition performance and flame stability, increasing effective combustion area, and broadening working range
Pending Publication Date: 2020-02-07
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS +1
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Problems solved by technology
However, the radial flame stabilizer will block the flow channel and increase the flow velocity in the duty flame stabilizer. At the same time, the low-velocity recirculation zone formed behind the radial stabilizer will also entrain the flow in the duty area and destroy the flow form of the duty area, thereby deteriorating the combustion chamber. On-duty ignition performance and flame stabilization capability
Method used
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Embodiment 1
[0025] Embodiment 1: A pneumatically assisted concave cavity support plate flame stabilizer in this embodiment includes a front duct diverter plate 1, a concave cavity flame stabilizer 2 connected to the rear end of the front duct diverter plate 1, and is arranged on The back channel splitter plate 3 and the support plate flame stabilizer 4 at the rear end of the cavity flame stabilizer 2 .
[0026] The direction from the front end / side to the rear end / side described in this embodiment is the flow direction of the airflow entering the combustion chamber, which is also the axial direction described in this embodiment ( image 3 in the X-axis direction). The radial direction described in this embodiment is the direction from the upper end / side of the combustion chamber to the lower end / side ( image 3 in the Y-axis direction).
[0027] The combustion chamber described in this embodiment is an existing structure, and the outer wall of the combustion chamber refers to the wall s...
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The invention discloses a pneumatic auxiliary type cavity support plate flame stabilizer. The pneumatic auxiliary type cavity support plate flame stabilizer comprises a front duct splitter plate, a cavity flame stabilizer body connected with the rear end of the front duct splitter plate, a rear duct splitter plate arranged at the rear end of the cavity flame stabilizer body and a support plate flame stabilizer body, wherein the front duct splitter plate comprises a first splitter plate body which gradually extends in the direction away from the outer wall of a combustion chamber in the airflowinflow direction; the rear end of the first splitter plate body is connected with a second splitter plate body which extends in the horizontal direction; the support plate flame stabilizer body is fixed to the lower surface of the second splitter plate body; and the second splitter plate body is provided with a plurality of first flow channels used for allowing outer duct gas to flow into a cavity of the cavity flame stabilizer body. According to the pneumatic auxiliary type cavity support plate flame stabilizer, the ignition and flame stabilization capacity of the cavity support plate flamestabilizer body is improved, and the cavity support plate flame stabilizer has wider ignition and flameout boundary conditions compared with a conventional cavity support plate flame stabilizer.
Description
technical field [0001] The invention relates to a flame stabilizer used in a turbofan engine afterburner combustion chamber, a sub-combustion ramjet engine combustion chamber and a turbofan / ramjet combined cycle engine multi-mode combustion chamber, in particular to a pneumatically assisted concave cavity support plate flame stabilizer. Background technique [0002] Turbine-based combined cycle (TBCC) as an air-breathing engine has the advantages of wide flight range, conventional take-off and landing, and reusability, and is considered to be the most promising hypersonic vehicle power at this stage. device. Due to the large variation of the bypass ratio in the whole working range, the low temperature of the incoming flow inside the TBCC multi-mode combustor and the excessive local flow velocity bring difficulties to the ignition and flame stability inside the multi-pass combustor. [0003] With the increase of the airflow velocity in the modern high-performance afterburne...
Claims
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IPC IPC(8): F23R3/20F23R3/28
CPCF23R3/20F23R3/28
Inventor 范育新缪俊杰赵世龙吴伟秋刘天池
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS