A Study on the Installed Performance Seeking Control for Aero-Propulsion under Supersonic State
-
Fengyong Sun
,
Lizhen Miao
Abstract
An integrated model including inlet, engine and nozzle with their internal and external characteristics was built to simulate the propulsion installed performance. With the integrated model, a new performance seeking control scheme under supersonic state is firstly proposed, taking inlet ramp angle as optimizing variable, which is equally important to fuel flow rate, nozzle throat area, guided vane angle of fan and compressor. Specially, engine installed thrust replaces its total thrust as one crucial factor for performance seeking control. Installed performances under supersonic state are significantly improved with the new scheme, as installed thrust increases of up to 4.9% in the maximum thrust mode, installed specific fuel consumption improvements of up to 3.8% in the minimum fuel consumption mode, and turbine temperature decreases of up to 0.6% in the minimum turbine temperature mode. The simulation results also indicates that, the performance seeking control scheme proposed shows superiority in restraining of the increasing of rotational speed and turbine temperature in performance seeking control.
Funding statement: Funding: Aeronautical Science Foundation of China (Grant/Award Number: ‘20142152022’) Funding of Jiangsu Innovation Program for Graduate Education (Grant/Award Number: ‘KYLX15_0257’).
Nomenclature
- A8
Nozzle Throat Area
- A9
Nozzle Exit Area
- A10
Nozzle Maximum Cross-sectional Area
- Adbl
Inlet Boundary Layer Flow Tube Area
- Ac
Inlet Capture Area
- Cspill
Inlet Spill Drag Coefficient
- Cdbl
Inlet Boundary Layer Drag Coefficient
- Caft
Nozzle Aft-body Drag Coefficient
- αf
Fan Vane Angle
- αc
Compressor Vane Angle
- F
Engine Total Thrust
- Fin
Installed Engine Thrust
- σ
Inlet Total Pressure Recovery Coefficient
- φ
Inlet Flow Coefficient
- δ
Inlet Ramp Angle
- ρ
Air Density
- εin
Error of Inlet and Engine Cooperation Working Equation
- εen
Errors of Engine Component Cooperation Working Equations
- Ma
Mach Number
- H
Flight Height
- T
Temperature
- p
Pressure
- Pnf
Fan Rotational Speed
- Pnc
Compressor Rotational Speed
- Smf
Fan Surge Margin
- Smc
Compressor Surge Margin
- Smi
Inlet Surge Margin
- Wfb
Fuel Flow Rate
- sfc
Specific Fuel consumption
- sfcin
Installed Specific Fuel consumption
- Fspill
Inlet Spill Drag
- Fdbl
Inlet Boundary Layer Drag
- Faft
Aft-body Drag
- men
Engine Air Flow
Engine Station Number
- 0
Free Stream
- 1
Inlet of Supersonic Inlet
- 2
Inlet of Fan
- 46
Outlet of Fan Turbine
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©2016 by De Gruyter
Articles in the same Issue
- Frontmatter
- Full-Range Mathematical Modeling of Turboshaft Engine in Aerospace
- Modeling and HIL Simulation of Flight Conditions Simulating Control System for the Altitude Test Facility
- Investigation of Detailed Flow in a Variable Turbine Nozzle
- A Study on the Installed Performance Seeking Control for Aero-Propulsion under Supersonic State
- Study of the Standard k-ε Model for Tip Leakage Flow in an Axial Compressor Rotor
- Experimental Study of Propulsion Performance by Single-Pulse Rotating Detonation with Gaseous Fuels-Oxygen Mixtures
- Finite Element Analysis for Turbine Blades with Contact Problems
- CFD Modeling of Mixed-Phase Icing
- Effect of Steam Addition on the Flow Field and NOx Emissions for Jet-A in an Aircraft Combustor
- An Integrated Optimization Design Method Based on Surrogate Modeling Applied to Diverging Duct Design
- Numerical Study of Unsteady Properties of Ethylene/Air Turbulent Jet Diffusion Flame with Detached Eddy Simulation
- Influence of Rotor-Stator Interaction on Flow Stability in Centrifugal Pump Based on Energy Gradient Method
Articles in the same Issue
- Frontmatter
- Full-Range Mathematical Modeling of Turboshaft Engine in Aerospace
- Modeling and HIL Simulation of Flight Conditions Simulating Control System for the Altitude Test Facility
- Investigation of Detailed Flow in a Variable Turbine Nozzle
- A Study on the Installed Performance Seeking Control for Aero-Propulsion under Supersonic State
- Study of the Standard k-ε Model for Tip Leakage Flow in an Axial Compressor Rotor
- Experimental Study of Propulsion Performance by Single-Pulse Rotating Detonation with Gaseous Fuels-Oxygen Mixtures
- Finite Element Analysis for Turbine Blades with Contact Problems
- CFD Modeling of Mixed-Phase Icing
- Effect of Steam Addition on the Flow Field and NOx Emissions for Jet-A in an Aircraft Combustor
- An Integrated Optimization Design Method Based on Surrogate Modeling Applied to Diverging Duct Design
- Numerical Study of Unsteady Properties of Ethylene/Air Turbulent Jet Diffusion Flame with Detached Eddy Simulation
- Influence of Rotor-Stator Interaction on Flow Stability in Centrifugal Pump Based on Energy Gradient Method
