Experimental and computational
                                                investigation into the use of co-flow fluidic thrust
                                                vectoring on a small gas turbine

Banazadeh, Afshin; Saghafi, Fariborz; Ghoreyshi, Mehdi; Pilidis, Pericles

doi:10.1017/s0001924000001950

Cited by 21 publications

(20 citation statements)

References 15 publications

(14 reference statements)

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“…The present results for the effect of varying secondary gap height on thrust vectoring angle at constant Coanda surface radius shown in Figure 6-8 are in good agreement with the results of (the experimental and numerical work) of [14] shown in Figure 13, and with (the experimental and numerical work) of [12] shown in Figure 14.…”

Section: Verification Of Resultssupporting

confidence: 87%

Experimental Study of Jet Vectoring by using Counter Flow at Subsonic Speed in Circular Jet

Al-Asady¹,

Faseeh²

2017

IJCA

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An experimental investigation of fluidic jet vectoring using counter-flow method had been carried out in this current work. The experimental investigation included a set of experiments to examine the various effects of geometric variables on the thrust vectoring angle. These included Coanda surface radius R/d = (0.58823, 1.17647, 1.75471), secondary gap height h/d = (0.02941, 0.05882), and secondary mass flow ratio range of (0 ≤ S / p ≤ 0. 07882). In addition, the test rig was built to display the ability of counter-flow method to vector the primary flow in pitch and yaw axes. Load cell readings were obtained using two components overhead balance. The results show proportional increase in vectoring angle value with the increase of the secondary suction rate. Three zones can be observed: a "dead zone" region at low mass flow ratios, followed by a control region where continuous primary jet control is achievable until a saturation region is reached. Small Coanda surface ratio resulted in an extended dead zone. The secondary gap height increase had an inverse effect on the thrust vectoring angle. A Smoke visualization was carried out to augment the experimental work and to demonstrate primary flow vectoring in pitch, and yaw axes. The investigation shows that the experimental gave a good agreement compared with previous studies on jet vectoring angle.

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Section: Verification Of Resultssupporting

confidence: 87%

Experimental Study of Jet Vectoring by using Counter Flow at Subsonic Speed in Circular Jet

Al-Asady¹,

Faseeh²

2017

IJCA

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“…All thrust vectoring techniques are evaluated with some common parameters such as: pitch thrust vector angle and thrust vectoring efficiency, which are important parameters to evaluate and compare the ability of different configurations to vector the primary exhaust flow with a given amount of secondary fluidic injection (Kowal, 2002;Flamm, 1996). The fluidic thrust vectoring techniques have been developed to include co-flow, counter-flow, shock vector control, throat skewing, and synthetic jet actuators (Jain et al, 2015;Banazadeh et al, 2008). All these vectoring techniques use secondary jet flows for thrust vectoring.…”

Section: Introductionmentioning

confidence: 99%

Numerical Investigation of Optimization of Injection Angle Effects on Fluidic Thrust Vectoring

Forghany

Taeibi-Rahni

Ghohieh

2017

JAFM

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A computational investigation was conducted to optimize the fluidic injection angle effects on thrust vectoring. Numerical simulation of fluidic injection for shock vector control, with a convergent-divergent nozzle concept was performed, using URANS approach with Spalart-Allmaras turbulence model. The fluidic injection angles from 60º to 120º were investigated at different aerodynamic and geometric conditions. The current investigation demonstrated that secondary injection angle is an essential parameter in fluidic thrust vectoring. Computational results indicated that, optimizing secondary injection angle would have positive impact on thrust vectoring performance. Furthermore, in most cases, decreasing expansion ratio of the nozzle with increasing NPR has negative impact on pitch thrust vector angle and thrust vectoring efficiency. That is, the highest pitch thrust vector angle is obtained by decreasing nozzle expansion ratio with increasing SPR in smaller fluidic injection angles. In addition, the current investigation attempted to initiate a database of optimized injection angles with different essential parameter effects on thrust vectoring, in order to guide the design and development of an efficient propulsion system.

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“…3 and listed in Table 2, different nozzles including one rectangular and two circular sections have been built and experimentally tested to gather data for different secondary to primary mass flow ratios. To improve the validity of the results by increasing the number of data, other geometrically different nozzles have also been considered, some of which from a parallel investigation process on the nozzle geometry optimisation for the best thrust vectoring angle, and analysed computationally using a previously developed and validated CFD simulation models (15,19) . The validation of the models has been carried out by the use of the experimental test data of the already mentioned physically built nozzles.…”

Section: Introductionmentioning

confidence: 99%

An investigation of empirical formulation and design optimisation of co-flow fluidic thrust vectoring nozzles

Banazadeh

Saghafi

2016

Aeronaut. j.

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The purpose of this paper is to design and develop an advanced co-flow fluidic nozzle, based on the Coanda effect concept, for multi-directional thrust vectoring of small jet engines. Recent progress on finding an optimal geometry with a fixed momentum ratio to achieve maximum thrust deflection angle is discussed here. The efficiency of the system is found to be a weakly nonlinear function of the secondary to primary flow momentum as well as three geometric parameters. A useful empirical formulation is derived for thrust vectoring angle, based on a series of tests carried out on different nozzles. An accurate computational fluid dynamics model is also developed and evaluated against the experimental data. Moreover, quasi-Newton optimisation algorithm is employed to find an optimal geometry with a constant relative jet momentum and a constant secondary slot size. In this technique, the optimal wall geometric parameters are calculated in the direction of the steepest gradient with the help of the numerical simulation model in every iteration step. Additionally, an optimised fluidic nozzle is constructed to experimentally verify the numerical results and the empirical equation.

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Experimental and computational investigation into the use of co-flow fluidic thrust vectoring on a small gas turbine

Cited by 21 publications

References 15 publications

Experimental Study of Jet Vectoring by using Counter Flow at Subsonic Speed in Circular Jet

Experimental Study of Jet Vectoring by using Counter Flow at Subsonic Speed in Circular Jet

Numerical Investigation of Optimization of Injection Angle Effects on Fluidic Thrust Vectoring

An investigation of empirical formulation and design optimisation of co-flow fluidic thrust vectoring nozzles

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