Shock vector control (SVC) based on transverse jet injection is one of the fluidic thrust vectoring (FTV) technologies, and is considered as a promising candidate for the future exhaust system working at high nozzle pressure ratio (NPR). However, the low vector efficiency (η) of the SVC nozzle remains an important problem. In the paper, a new method, named as the improved SVC, was proposed to improve the vector efficiency (η) of a SVC nozzle, which enhances the vector control of primary supersonic flow by adopting a bypass injection. It needs less secondary flow from high pressure component of an aero-engine and has smaller influence on the working character of an aero-engine. The flow mechanism of the improved SVC nozzle was investigated by solving three-dimensional Reynolds-averaged Navier--Stokes with shear stress transport (SST) κ–ω turbulence model. The shock waves, jets-primary flow interactions, flow separation, and vector performance were analyzed. The influences of aerodynamic and geometric parameters, namely, NPR, secondary pressure ratio (SPR), and bypass injection position (Xj.ad.) on flow characteristics and vector performance were investigated. Based on the design of experiment (DOE), the response surface methodology (RSM) and the simulation model of an aero-engine, a method to estimate the coupling performance of the improved SVC nozzle and an aero-engine was studied, and a new balance relationship between the improved SVC nozzle and an aero-engine was established. Results shows that (1) with the assistance of bypass injection, the jet penetration and the capability of vector control are largely improved, resulting in a vector efficiency (η) of 1.98 deg/%-ω at the designed NPRD = 13.88; (2) in a wide range of operating conditions, larger vector angle (δp), higher thrust coefficient (Cfg), and higher vector efficiency (η) of the improved SVC nozzle were obtained, (3) in the coupling process of the improved SVC nozzle and an aero-engine, a δp of 18.1 deg was achieved at corrected secondary flow ratio of 10% and corrected bypass ratio of 6.98%, and the change of the thrust and the specific fuel consumption (SFC) were within 12%, which is better than the coupling performance of a SVC nozzle and an aero-engine.

References

References
1.
Scharnhorst
,
R. K.
,
2013
, “
Characteristics of Future Military Aircraft Propulsion System
,”
AIAA
Paper No.
2013-446.
2.
Gal-Or
,
B.
,
1990
, “
The Fundamental Concepts of Vectored Propulsion
,”
J. Power Propul.
,
6
(
6
), pp.
747
757
.
3.
Allen
,
J. E.
,
Armstrong
,
F. W.
, and
Denning
,
R. M.
,
1995
, “
Evolution of Aviation and Propulsion Systems: The Next Fifty Years
,”
Proc. Inst. Mech. Eng., Part G
,
209
(
1
), pp.
15
33
.
4.
Mason
,
M. S.
, and
Crowther
,
W. J.
,
2004
, “
Fluidic Thrust Vectoring for Low Observable Air Vehicle
,”
AIAA
Paper No. 2004-2210.
5.
Atesoglu
,
O.
, and
Ozgoren
,
M. K.
,
2007
, “
High-Alpha Flight Maneuverability Enhancement of a Fighter Aircraft Using Thrust Vectoring Control
,”
J. Guid., Control, Dyn.
,
30
(
5
), pp.
1480
1493
.
6.
Vinayagam
,
A. K.
, and
Sinha
,
N. K.
,
2013
, “
Optimal Aircraft Take-Off With Thrust Vectoring
,”
Aeronaut. J.
,
117
(
1197
), pp.
1119
1137
.
7.
Young
,
J. B.
,
2004
, “
X-31 Vector Program Summary
,”
AIAA
Paper No. 2004-5026.
8.
Vinayagam
,
A. K.
, and
Sinha
,
N. K.
,
2014
, “
An Assessment of Thrust Vector Concepts for Twin-Engine Airplane
,”
Proc. Inst. Mech. Eng. Part G.
,
228
(
6
), pp.
960
979
.
9.
Wilde
,
P. I. A.
,
Gill
,
K.
, and
Michie
,
S. N.
,
2008
, “
Integrated Design of Fluidic Flight Controls for a Flapless Aircraft
,”
AIAA
Paper No. 2008-164.
10.
Deere
,
K. A.
,
2003
, “
Summary of Fluidic Thrust Vectoring Research Conducted at NASA Langley Research Center
,”
AIAA
Paper No. 2003-3800.
11.
Strykowski
,
P. J.
,
Krothapalli
,
A.
, and
Forliti
,
D. J.
,
1996
, “
Counterflow Thrust Vectoring of Supersonic Jets
,”
AIAA J.
,
34
(
11
), pp.
2306
2314
.
12.
Heo
,
J. Y.
, and
Sung
,
H. G.
,
2012
, “
Fluidic Thrust Vector Control of Supersonic Jet Using Co-Flow Injection
,”
J. Propulsion Power
,
28
(
4
), pp.
858
861
.
13.
Miller
,
D. N.
,
Yagle
,
P. J.
, and
Hamstra
,
J. W.
,
1999
, “
Fluidic Throat Skewing for Thrust Vectoring in Fixed-Geometric Nozzles
,”
AIAA
Paper No. 1999-16262.
14.
Deere
,
K. A.
,
Berrier
,
B. L.
, and
Flamm
,
J. D.
,
2003
, “
Computational Study of Fluidic Thrust Vectoring Using Separation Control in a Nozzle
,”
AIAA
Paper No. 2003-3803.
15.
Zhang
,
J. D.
, and
Wang
,
Z. X.
,
2012
, “
Numerical Research on Two Types of Fluidic Thrust Vector
,”
Acta Aerodyanmica Sin.
,
30
(
2
), pp.
205
209
.http://kqdlxxb.cars.org.cn/CN/volumn/volumn_1203.shtml
16.
Hsia
,
H. T.
,
1966
, “
Injection Equivalence of Secondary Injection to a Blunt Body in Supersonic Flow
,”
AIAA J.
,
4
(
10
), pp.
1832
1834
.
17.
Broadwell
,
J. E.
,
1963
, “
Analysis of the Fluid Mechanics of Secondary Injection for Thrust Vector Control
,”
AIAA J.
,
1
(
5
), pp.
1065
1075
.
18.
Wilson
,
W.
, and
Comparin
,
R.
,
1970
, “
Analysis of the Flow-Disturbance and Side Forces Due to Gaseous Secondary Injection Into a Rocket Nozzle
,”
J. Spacecr.
,
7
(
5
), pp.
439
543
.
19.
Waithe
,
K. A.
, and
Deere
,
K. A.
,
2003
, “
Experimental and Computational Investigation of Multiple Injection Ports in a Convergent-Divergent Nozzle for Fluidic Thrust Vectoring
,”
AIAA
Paper No. 2003-3802.
20.
Shi
,
J. W.
,
Wang
,
Z. X.
,
Zhou
,
L.
, and
Zhang
,
X. B.
,
2016
, “
Investigation on Flow-Field Characteristics of Shock Vector Controlling Nozzle Based on Confined Transverse Injection
,”
ASME J. Eng. Gas Turbines Power
,
138
(
10
), pp.
1
10
.
21.
Zmijanovic
,
V.
,
Leger
,
L.
,
Depussay
,
E.
,
Sellam
,
M.
, and
Chpoun
,
A.
,
2016
, “
Experimental-Numerical Parametric Investigation of a Rocket Nozzle Secondary Injection Thrust Vectoring
,”
J. Propul. Power
,
32
(
1
), pp.
196
213
.
22.
Hamed
,
A.
, and
Laskowski
,
G.
,
1997
, “
A Parametric Study of Slot Injection Thrust Vectoring in a 2D CD Nozzle
,”
AIAA
Paper No. 1997-3154.
23.
Deng
,
R. Y.
,
Kong
,
F. S.
, and
Kim
,
H. D.
,
2014
, “
Numerical Simulation of Fluidic Thrust Vectoring in an Axisymmetric Supersonic Nozzle
,”
J. Mech. Sci. Technol.
,
28
(
12
), pp.
4979
4987
.
24.
Sellam
,
M.
,
Zmijanovic
,
V.
,
Leger
,
L.
, and
Chpoun
,
A.
,
2015
, “
Assessment of Gas Thermodynamic Characteristics on Fluidic Thrust Vectoring Performance: Analytical, Experimental and Numerical Study
,”
Int. J. Heat Fluid Flow
,
53
, pp.
156
66
.
25.
Chiarelli
,
C.
,
Johnsen
,
R. K.
, and
Shieh
,
C. F.
,
1993
, “
Fluidic Scale Model Multi-Plane Thrust Vector Control Test Results
,”
AIAA
Paper No. 93-2433.
26.
Wing
,
D. J.
,
1994
, “
Static Investigation of Two Fluidic Thrust-Vectoring Concepts on a Two-Dimensional Convergent—Divergent Nozzle
,” National Aeronautics and Space Administration, Washington, DC, Report No.
TM-4574
.https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19950012627.pdf
27.
Giuliano
,
V. J.
, and
Wing
,
D. J.
,
1997
, “
Static Investigation of a Fixed-Aperture Nozzle Employing Fluidic Injection for Multiaxis Thrust Vector Control
,”
AIAA
Paper No. 97-3149.
28.
Williams
,
R. G.
, and
Vittal
,
B. R.
,
2002
, “
Fluidic Thrust Vectoring and Throat Control Exhaust Nozzle
,”
AIAA
Paper No. 2002-4060.
29.
Ali
,
A.
,
Rodriguez
,
C. G.
,
Neely
,
A. J.
, and
Young
,
J.
,
2012
, “
Combination of Fluidic Thrust Modulation and Vectoring in a 2D Nozzle
,”
AIAA
Paper No. 2012-3780.
30.
Anderson
,
C. J.
,
Giuliano
,
V. J.
, and
Wing
,
D. J.
,
1997
, “
Investigation of Hybrid Fluidic/Mechanical Thrust Vectoring for Fixed-Exit Exhaust Nozzles
,”
AIAA
Paper No. 97-3148.
31.
Shi
,
J. W.
,
Wang
,
Z. X.
,
Zhang
,
X. B.
, and
Zhou
,
L.
,
2017
, “
Investigation on a Hybrid SVC Nozzle and Coupling Performance Estimation With Aero-Engine
,”
AIAA
Paper No. 2017-5079.
32.
Sriram
,
A. T.
, and
Mathew
,
J.
,
2004
, “
Numerical Prediction of Two-Dimensional Transverse Injection Flows
,”
AIAA
Paper No. 2204-1099.
33.
Zhang
,
Q.
, and
Yang
,
Y.
,
2012
, “
Some Comparative of Turbulence Models for Fluidic Thrust Vectoring Nozzle
,”
J. Northwest. Polytech. Univ.
,
31
(
1
), pp.
62
67
.
34.
Spaid
,
F. W.
, and
Zukoski
,
E. E.
,
1968
, “
A Study of the Interaction of Gaseous Jets From Transverse Slot With Supersonic External Flows
,”
AIAA J.
,
6
(
2
), pp.
205
212
.
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