Design and combustion characteristics analysis of a static shaft turbofan engine
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Rong Ma
Abstract
A design scheme of a static shaft turbofan engine is proposed to meet the requirements of light weight and large thrust weight ratio of small aeroengine. As the core component of stable combustion, the thermal protection problem of the mid-mounted combustion chamber is particularly prominent. This paper designs a mid-mounted combustion chamber configuration that combines gas film cooling and central combustion. The influence of structural parameters on combustion characteristics is explored by numerical simulation, and the theoretical design and numerical simulation is verified based on combustion test results. The results show that the flame shape of the mid-mounted combustion chamber conforms to the characteristics of central combustion. The combustion effect of the nozzle with spray angle of 45° and flow rate of 1.87 kg/h meets the requirements of secondary combustion of the static shaft turbofan engine, and the air inlet of the combustion liner effectively increases the thickness of the cooling gas film. The experimental results are in good agreement with the numerical simulation results, and the temperature of the combustion liner wall can be reduced effectively. The above research provides a theoretical basis for the combustion chamber design of small static shaft turbofan engines and a reference for the thermal protection methods of small aeroengine combustion chambers.
Funding source: National Science and Technology Major Project
Award Identifier / Grant number: J2019-IV-0003-0070
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Author contributions: All the authors have accepted responsibility for the entire content of this submitted manuscript and approved submission.
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Research funding: This work was supported by the National Science and Technology Major Project (J2019-IV-0003-0070).
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
Nomenclature
- H 1
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the total length of the combustion chamber, m
- D 1
-
the maximum outer diameter of the combustion chamber, m
- d 1
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the inner diameter of the shell, m
- A 1
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the sectional area of the combustion chamber, m2
- A 2
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the sectional area of the combustion liner, m2
- D 2
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the outer diameter of combustion liner, m
- d 2
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the inner diameter of the combustion liner, m
- D 2max
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the maximum section outer diameter of the combustion liner expansion section, m
- d 2max
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the maximum section inner diameter of the combustion liner expansion section
- L 2
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the axial length of combustion liner, m
- Q e
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the air flow at the air inlet of combustion liner, L/min
- V e
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the air inlet velocity, m/s
- n e
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the number of air inlets
- d e
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the diameter of the air inlet, m
-
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mass air flow into combustion chamber, kg/s
-
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mass flow of fuel into combustion chamber, kg/s
- f
-
fuel-air ratio
- α
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the excess air coefficient
- L s
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the total length of swirler, m
- D 1s
-
primary swirler outer diameter, m
- d 1s
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primary swirler inner diameter, m
- S 1
-
primary swirl number
- θ 1s
-
primary swirler blade mounting angle
- D 2s
-
secondary swirler outer diameter, m
- d 2s
-
secondary swirler inner diameter, m
- S 2
-
secondary swirl number
- θ 2s
-
secondary swirler blade mounting angle
- S n
-
the swirl number
- Z
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the hub ratio of swirler
- θ ns
-
blade mounting angle
- k s
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the ratio of primary and secondary air flow
- Q 1s
-
the air inflow of the primary swirler, kg/s
- Q 2s
-
the air inflow of the secondary swirler, kg/s
- A 1s
-
the area of the primary air inlet channel, m2
- A 2s
-
the area of the secondary air inlet channel, m2
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© 2023 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Proper Orthogonal Decomposition analysis of mode switching in supersonic jets impinging on flat and corrugated plates
- Impact of cavity and ramp configuration on the combustion performance of a strut-based scramjet combustor
- In-service load calculation surrogate models for high-pressure turbine blade life digital twin
- Numerical analysis on the effect of passive control geometry in supersonic jet mixing enhancement
- Study on one-dimensional performance prediction of multi-stage axial turbine based on the blade height
- Dynamic characteristics of open-ends squeeze film dampers with air ingestion
- Fluid flow in a microdiffuser at small Reynolds numbers
- A study on optimal rotor speed control method for helicopter power system considering the influence of infrared suppressors
- Effects of turbulence and flamelet combustion modelling on the CFD simulation of a dual inlet ramjet combustor
- Design and combustion characteristics analysis of a static shaft turbofan engine
- Aerothermal effects of squealer openings on a cavity tip in a turbine cascade
- Endwall heat transfer in wedge channel with teardrop pin fins, circular fins and oblong pin fins
- Virtual deflection with synthetic jet actuators at high angles of attack
- Design of mode transition control system for tandem TBCC engine based on direct performance parameters closed-loop control
- Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0
- Influence of the ending position of controllable speed casing on a transonic compressor rotor tip leakage flow
- Integrated modeling and coupling characteristics analysis of helicopter/engine/infrared suppressor
- Effect of velocity ratio and Mach number on thin lip coaxial jet
- C conjugate heat transfer simulation of swirl internal cooling on blade leading edge
- Influence of inlet structure on combustion flow structure in magnesium powder fueled water ramjet engine
- Research on high-bandwidth linear active disturbance rejection control method for variable speed turboshaft engine
- Numerical investigation of force over the horizontal jet tab of various sector angle fixed to the convergent-divergent nozzle exit
Artikel in diesem Heft
- Frontmatter
- Proper Orthogonal Decomposition analysis of mode switching in supersonic jets impinging on flat and corrugated plates
- Impact of cavity and ramp configuration on the combustion performance of a strut-based scramjet combustor
- In-service load calculation surrogate models for high-pressure turbine blade life digital twin
- Numerical analysis on the effect of passive control geometry in supersonic jet mixing enhancement
- Study on one-dimensional performance prediction of multi-stage axial turbine based on the blade height
- Dynamic characteristics of open-ends squeeze film dampers with air ingestion
- Fluid flow in a microdiffuser at small Reynolds numbers
- A study on optimal rotor speed control method for helicopter power system considering the influence of infrared suppressors
- Effects of turbulence and flamelet combustion modelling on the CFD simulation of a dual inlet ramjet combustor
- Design and combustion characteristics analysis of a static shaft turbofan engine
- Aerothermal effects of squealer openings on a cavity tip in a turbine cascade
- Endwall heat transfer in wedge channel with teardrop pin fins, circular fins and oblong pin fins
- Virtual deflection with synthetic jet actuators at high angles of attack
- Design of mode transition control system for tandem TBCC engine based on direct performance parameters closed-loop control
- Effect of tab shape, length, and placement on the over-expanded free jet at Mach 2.0
- Influence of the ending position of controllable speed casing on a transonic compressor rotor tip leakage flow
- Integrated modeling and coupling characteristics analysis of helicopter/engine/infrared suppressor
- Effect of velocity ratio and Mach number on thin lip coaxial jet
- C conjugate heat transfer simulation of swirl internal cooling on blade leading edge
- Influence of inlet structure on combustion flow structure in magnesium powder fueled water ramjet engine
- Research on high-bandwidth linear active disturbance rejection control method for variable speed turboshaft engine
- Numerical investigation of force over the horizontal jet tab of various sector angle fixed to the convergent-divergent nozzle exit
