22nd Congress of International Council of the Aeronautical Sciences, Harrogate, UK, 28 August - 1st September, 2000
Paper ICAS 2000-5.3.4

EXPERIMENTAL INVESTIGATION OF STATIC INTERNAL PERFORMANCE FOR AN AXISYMMETRIC VECTORING THRUST NOZZLE (AVEN)

J. Jin, J. Zhao, M. Zhang, C. Lai
Chinese Gas Turbine Establishment, PRC

Keywords: upersonic test, thrust determination, thrust vectoring nozzle

An investigation has been conducted in the static nozzle supersonic test facility of Chinese Gas Turbine Establishment to determine the internal performance characteristics of an axisymmetric vectoring thrust nozzle with multiaxis thrust-vectoring capability, which was achieved by deflection of the divergent section of nozzle. The effects of nozzle pressure ratio (NPR) on turning and thrust performance as well as the wall static pressure distributions were studied at varied nozzle geometric vector angle with three different nozzle geometries. The results of these investigations indicated that while the NPR was less than design pressure ratio, a peak resultant vector angle which was greater than the geometric vector angle occurred and the resultant vector angle was close to the geometric vector angle with the increase of NPR, as well as a peak thrust coefficient occurred near the design pressure ratio and the thrust coefficient slightly decreased with the increase of nozzle geometric vector angle. At lower NPR, the thrust coefficient was high due to flow separation in nozzle. These shown that vectoring of the exhaust flow could be achieved with essentially no addition turning losses within nozzle design pressure ratio compared with existing novectoring convergent-divergent exhaust nozzles.

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