Research on an optimization design method for a TBCC propulsion scheme
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Pinxin Wu
und
Dongqing Zhang
Abstract
An optimization methodology for a TBCC propulsion schemes was established for hypersonic vehicles, focusing on the integration of aircraft and engine performance. Altitude-velocity characteristics of TBCC propulsion were obtained through engine performance calculations. By analyzing mission requirements, lift-drag characteristics, and flight constraints, the take-off thrust-weight ratio and wing load of the vehicle were optimized to meet the flight conditions. In addition, the fuel ratio was calculated. To determine the vehicle’s gross take-off weight and the engine’s take-off thrust, a model considering the weight of the vehicle and the turbine engine were used. The optimization process selects four thermodynamic cycle parameters for the turbine engine as the independent variables. An improved particle swarm optimization-back propagation neural network was used to establish the relationship between the four parameters and the gross take-off weight, aiming to minimize the vehicle’s weight. The results of the optimization process show that the total take-off weight of the optimized vehicle has decreased from 112363.41 kg to 102218.98 kg. The required uninstalled take-off thrust of TBCC has also been reduced from 162.86 kN to 147.49 kN, resulting in a decrease in mass flow from 156.50 kg/s to 133.30 kg/s.
Acknowledgements
The authors would like to sincerely thank the faculty and colleagues at the School of Power and Energy, Northwestern Polytechnical University, for providing an intellectually stimulating environment that made this research possible. We would also like to extend a special thanks to the team at the Airbreathing Hypersonic Propulsion Laboratory, NWPU, for their valuable insights and contributions to the TBCC propulsion schemes discussed in this manuscript.
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Research ethics: Not applicable.
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Author contributions: The authors have accepted responsibility for the entire content of this manuscript and approved its submission.
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Competing interests: The authors state no conflict of interest.
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Research funding: None declared.
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Data availability: Not applicable.
Nomenclature
- a //
-
acceleration parallel to velocity (m/s2)
- B
-
bypass ratio
- c1, c2
-
acceleration coefficient
- C L
-
lift coefficient
- C D
-
drag coefficient
- D
-
drag force (N)
- dh/dt
-
climbing rate (m/s)
- dV/dt
-
acceleration rate (m/s2)
- g 0
-
acceleration of gravity (m/s2)
- L b
-
total length (m)
- L
-
lift force (N)
- L/D
-
lift-to-drag ratio
- m a
-
engine airflow(kg/s)
- MSE
-
mean square error
- n
-
the number of samples
- P s
-
weight specific excess power
- q
-
dynamic pressure (Pa)
- S
-
planform or reference area (m2)
- t
-
current number of iterations
- t max
-
maximum number of iterations
- T
-
Thrust (N)
- T SL
-
thrust at sea-level take-off (N)
- T SL/W TO
-
thrust loading at sea-level take-off
- TSFC
-
installed thrust specific fuel consumption (h−1)
- T t4
-
turbine inlet total temperature (K)
- T t7
-
afterburner exit total temperature (K)
- u
-
total drag-to-thrust ratio
- V
-
velocity (m/s)
- V TOT
-
total volume (m3)
- W f
-
final weight of mission segment (kg)
- W i
-
initial weight of mission segment (kg)
- W TO
-
gross take-off weight (kg)
- W TO/S
-
wing loading (Pa)
- α
-
T/T SL, coefficient of thrust
- β
-
W/W TO, coefficient of weight
- θ
-
flight path angle (°)
- θ i
-
actual output of the neural network
-
-
target output of the neural network
- π CL
-
low-pressure compressor pressure ratio
- π CH
-
high-pressure compressor pressure ratio
- σ i
-
inlet total pressure recovery coefficient
- ω
-
inertia weight
- AOA
-
angle of attack (°)
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© 2024 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Experimental and numerical investigations on controlled parameter selection methods for kerosene-fueled scramjet
- Thrust-matching and optimization design of turbine-based combined cycle engine with trajectory optimization
- Parametric analysis of thermal cycle of a short take-off and vertical landing engine
- Conjugate heat transfer analysis on double-wall cooling configuration including jets impingement and film holes with conformal pins
- Research on the design method of mode transition control law for Ma6 external parallel TBCC engine
- A new schedule method for compact propulsion system model
- Numerical investigation on mixing of heated confined swirling coaxial jets with blockage
- Finite element based dynamic analysis of a porous exponentially graded shaft system subjected to thermal gradients
- Numerical study on aerodynamic performance of an intake duct affected by ground effect
- Influence of metal magnesium addition on detonation initiation in shock wave focusing Pulse Detonation Engine
- Probabilistic analysis of solid oxide fuel-cell integrated with gas turbine
- Improving thermal performance of turbine blade with combination of circular and oblong fins in a wedge channel: a numerical investigation
- Investigation on effect of injector orifice diameter on injector atomization and combustion characteristics of pulse detonation combustor
- Research on cascade control method for turboshaft engine with variable rotor speed
- The overall film cooling performance of crescent holes
- Air tab location effect on supersonic jet mixing
- Design and analysis of air intake of subsonic cruise vehicle with experimental validation
- Research on an optimization design method for a TBCC propulsion scheme
- Performance analysis of a gas turbine engine via intercooling and regeneration- Part 2
- Effects of bleed pressure on shock-wave/boundary-layer interactions in a transonic compressor stator with suction holes
- Effect of asymmetric leading edge on transition of suction side
Artikel in diesem Heft
- Frontmatter
- Experimental and numerical investigations on controlled parameter selection methods for kerosene-fueled scramjet
- Thrust-matching and optimization design of turbine-based combined cycle engine with trajectory optimization
- Parametric analysis of thermal cycle of a short take-off and vertical landing engine
- Conjugate heat transfer analysis on double-wall cooling configuration including jets impingement and film holes with conformal pins
- Research on the design method of mode transition control law for Ma6 external parallel TBCC engine
- A new schedule method for compact propulsion system model
- Numerical investigation on mixing of heated confined swirling coaxial jets with blockage
- Finite element based dynamic analysis of a porous exponentially graded shaft system subjected to thermal gradients
- Numerical study on aerodynamic performance of an intake duct affected by ground effect
- Influence of metal magnesium addition on detonation initiation in shock wave focusing Pulse Detonation Engine
- Probabilistic analysis of solid oxide fuel-cell integrated with gas turbine
- Improving thermal performance of turbine blade with combination of circular and oblong fins in a wedge channel: a numerical investigation
- Investigation on effect of injector orifice diameter on injector atomization and combustion characteristics of pulse detonation combustor
- Research on cascade control method for turboshaft engine with variable rotor speed
- The overall film cooling performance of crescent holes
- Air tab location effect on supersonic jet mixing
- Design and analysis of air intake of subsonic cruise vehicle with experimental validation
- Research on an optimization design method for a TBCC propulsion scheme
- Performance analysis of a gas turbine engine via intercooling and regeneration- Part 2
- Effects of bleed pressure on shock-wave/boundary-layer interactions in a transonic compressor stator with suction holes
- Effect of asymmetric leading edge on transition of suction side
