The thrust vectoring performance of a novel nozzle mechanism was numerically investigated. The nozzle was designed for supersonic, air-breathing engines using published engine data, isentropic relationships, and piecewise quartic splines. The mechanism utilizes two staggered, adjustable ramps. A baseline inviscid numerical simulation without ramps verified the nozzle design by comparing the results to the analytical data. Nine ramp configurations were analyzed under steady-state turbulent viscous conditions, using two sets of inlet parameters corresponding to inlet conditions with and without an afterburner (AB). The realizable – model was used to model the turbulence field. Area-weighted integrals of the exit flow showed superior flow deflection with the nonafterburning inlet flow parameters. Calculations of the mean flow deflection angles showed that the flow can be deflected as much as 30 deg in a given direction with the largest ramp length and angle values. The smallest ramp length (less than 5% of the nozzle length) demonstrated as much as 21 deg in flow deflection.
Two-Dimensional Supersonic Thrust Vectoring Using Staggered Ramps
Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received October 7, 2016; final manuscript received December 29, 2016; published online March 28, 2017. Editor: David Wisler.
- Views Icon Views
- Share Icon Share
- Cite Icon Cite
- Search Site
Montes, C. F., and Davis, R. L. (March 28, 2017). "Two-Dimensional Supersonic Thrust Vectoring Using Staggered Ramps." ASME. J. Eng. Gas Turbines Power. August 2017; 139(8): 082605. https://doi.org/10.1115/1.4035848
Download citation file:
- Ris (Zotero)
- Reference Manager