An Integrated Throughflow Method for the Performance Analysis of Variable Cycle Compression Systems
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Baojie Liu
Abstract
A streamline curvature method based integrated throughflow analysis approach is newly developed to deal with component matching problems of variable cycle compression systems. The construction of variable cycle compression system is modularly modelled in the procedure. Splitting and confluent flow are elaborately disposed. A numerical method based on the “streamline floating” character of streamline curvature method is developed to model the function of forward variable area bypass injector. Moreover, extensive models used in the throughflow calculations, including minimum loss incidence, deviation and loss models were assessed, selected and modified. Finally, code validations were conducted on three representative traditional compressors, i. e. NASA rotor 67, NASA stage 37 and a custom-designed low-speed repeating four-stage compressor. Both the predicted overall characteristics and spanwise profiles agree reasonably well with the experimental data. The validated procedure was finally used to sketch the performance maps of a double bypass compression system under two different control rules, i. e. the first bypass throttling and the second bypass throttling. The results show some aspects of the difficulties and complications in operating a variable cycle compression system, and meanwhile, demonstrate the superiority of the newly developed integrated throughflow method.
Funding statement: This work was supported by the National Natural Science Foundation of China [grant numbers 51776010, 51790511, 51476004].
Acknowledgements
The authors would like to thank Aeroengine Simulation Research Center of Beihang University for the use of the Numeca software package.
Nomenclature
- c
blade chord
- CDe
endwall drag coefficient
- CDs
secondary flow drag coefficient
- Cp
pressure rise coefficient,
equivalent suction surface diffusion ratio
- e
quasi-orthogonal direction on the mean streamsurface
- f
mixing factor
- G
mass flow rate
- h
blade height
streamtube height ratio
total enthalpy
incidence angle
minimum loss incidence angle of zero-camber NACA 65 cascades
equivalent sand-grain roughness
mass flow blockage correction factor
minimum loss incidence angle blade shape correction factor
minimum loss deviation angle blade shape correction factor
minimum loss incidence angle thickness correction factor
minimum loss deviation angle thickness correction factor
- m
meridional direction
- Ma
Mach number
slope parameter of minimum loss incidence
slope parameter of minimum loss deviation
blade row number
- o
throat opening
- P
pressure
- Pt
total pressure
- q
quasi-orthogonal direction on meridional perspective
- r
radius
- rc
radius of streamline curvature
- R
gas constant for air
- Re
Reynolds number based on chord and blade row inlet relative velocity
- s
blade pitch
- S
entropy
- t
thickness of blade
- tc
height of clearance
- U
blade speed
- V
absolute velocity
- W
relative velocity
- Wi
range of incidence angle
- Z
number of blades in a blade row
relative flow angle measured from meridional direction
mean flow angle, eq. (19)
intersection angle of quasi-orthogonal and radial direction on meridional perspective
deviation angle
minimum loss deviation angle of zero-camber NACA 65 cascades
incidence induced deviation variation
manual controlled deviation correction
intersection angle of quasi-orthogonal on the mean streamsurface and radial direction
stagger angle
camber angle
blade angle from meridional direction
gas density
mean density of leakage flow
solidity
streamline slope angle
loss coefficient
- Subscript
- a
additional
- AVDR
axial velocity-density ratio,
- c
clearance
- choke
choke condition
- e
endwall
- hub
hub span
- m
meridional direction
- mid
middle span
- min
minimum loss condition
Mach number
- s
shock
- sonic
sonic condition
- stall
stall condition
- tip
tip span
circumferential direction
- 1
inlet condition
- 2
outlet condition
- 3D
three-dimensional
- Superscript
two-dimensional low-speed minimum loss condition
- Abbreviations
- LE
leading edge
- TE
trailing edge
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Articles in the same Issue
- Frontmatter
- Effect of orifice spacing on twin circular parallel compressible jets
- Design and Experiment of Casing Treatment for a Centrifugal Compressor
- An Integrated Throughflow Method for the Performance Analysis of Variable Cycle Compression Systems
- Aerodynamic Performance Characteristics of NACA 0010 Cascade with Gurney Flaps
- Study on a Quasi-Two-Dimensional Fan Model for Variant Bypass-Ratio Condition
- Co-Flowing Jet Control Using Lip Thickness Variation
- Investigation on the Effect of Different Lands on Trailing Edge Slot Film Cooling
- Installation Characteristics of Variable Cycle Engine Based on Inlet Flow Matching
- Supersonic Jet Control by Tabs with Slanted Perforation
- Effect of Injection Angle on Performance of Full Coverage Film Cooling with Opposite Injection Holes
Articles in the same Issue
- Frontmatter
- Effect of orifice spacing on twin circular parallel compressible jets
- Design and Experiment of Casing Treatment for a Centrifugal Compressor
- An Integrated Throughflow Method for the Performance Analysis of Variable Cycle Compression Systems
- Aerodynamic Performance Characteristics of NACA 0010 Cascade with Gurney Flaps
- Study on a Quasi-Two-Dimensional Fan Model for Variant Bypass-Ratio Condition
- Co-Flowing Jet Control Using Lip Thickness Variation
- Investigation on the Effect of Different Lands on Trailing Edge Slot Film Cooling
- Installation Characteristics of Variable Cycle Engine Based on Inlet Flow Matching
- Supersonic Jet Control by Tabs with Slanted Perforation
- Effect of Injection Angle on Performance of Full Coverage Film Cooling with Opposite Injection Holes
