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Numerical Analysis of Non-Classical Isolators’ Flow Characteristics and Aerodynamic Performance

Author: WangWeiXing
Tutor: HuangGuoPing
School: Nanjing University of Aeronautics and Astronautics
Course: Aerospace Propulsion Theory and Engineering
Keywords: Isolator Cross-sectional shape Back pressure characteristics Hypersonic inlet Numerical Simulation
CLC: V231.3
Type: Master's thesis
Year: 2008
Downloads: 76
Quote: 1
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Abstract


Isolator hypersonic propulsion system key pneumatic components, the performance impact on promoting the stability margin of the system. -Sectional shape of the isolator, the isolator length equivalent diameter than the two main factors that affect the performance of the isolator, this article in length and equivalent diameter than the same premise, isolated segments of three different cross-section types (oval isolated segment, side turn oval isolated segment and rectangular isolated segment) to a three-dimensional numerical simulation. Analysis of isolated segments in the different sectional shape of the flow field, summarize the performance impact on the isolated segments of the cross-sectional shape change rule, given different to flow under the conditions of isolated segments outlet parameters trend for future unconventional isolated segments provide a reference design. First analysis of its internal flow field characteristics of the cross-sectional shape of the isolator. The study found that the isolated segments of different cross-sectional shapes, different characteristics of the flow field and shock train structure, thereby affecting its anti-pressure capability. The results show that, under uniform flow conditions, stream Mach number is less than 2, the flow field and shock train structure basic symmetry; stream Mach number is greater than 2, the flow field and shock train structure asymmetry shock train no longer isolator geometric center line of symmetry, as the stream Mach number increases, this asymmetry is exacerbated. Secondly, the cross-sectional shape of the isolated segment of its aerodynamic performance. Comparative analysis found that oval isolated segment of anti-pressure ability, isolated segment, followed by party turn oval, rectangle isolated segment weakest. Isolated section of the oval-shaped anti-pressure capacity ratio decreases gradually increased as the length of the axle length Axle ratio 1:00 strongest (ie round), isolated segment of anti-pressure ability; side turn oval isolated segment anti-pressure capacity is limited by the cross-sectional variation impact; rectangular isolated segment of anti-pressure capability diminishes as the aspect ratio increases. The results show that the cross-sectional shape of the isolator exit Mach number and temperature rise than the basic no effect on the export total pressure recovery significantly affected. Which, circular isolated segment of the total pressure recovery largest the the side turn oval isolation segment total pressure recovery smallest. To flow conditions on the performance of the isolator. The results showed that the isolated segment of anti-pressure capability with the free stream Mach number increases gradually increased, while exports total pressure recovery and Mach number decreases temperature rise than the rise. The study found that, for the segment of oval isolation, under different Mach number, when the isolator to withstand the maximum back pressure, the exit Mach number is basically the same.

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CLC: > Aviation, aerospace > Aviation > Aero-engine ( propulsion system ) > Engine theory > Aero-engine gas mechanics
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