# Axial turbine
#
# A repeating-stage axial turbine with two blade rows.

# New working directory for each invocation
workdir: runs/*

# Perfect gas inlet reprensentative of a gas turbine
inlet:
  Po: 16.0e5
  To: 1600.
  cp: 1100.
  gamma: 1.33

# Set viscosity by vane Reynolds number
Re_surf: 5e5

# Design variables for an axial turbine
mean_line:
  type: axial_turbine
  # Duty
  mdot: 500.
  rrms: 1.0
  # Aerodynamics
  psi: 1.6
  phi2: 0.6
  Ma2: 0.7
  fac_Ma3_rel: 1.0
  zeta: [1.0, 1.0]
  # Guess of loss
  Ys: [0.02, 0.05]

# Prescribe the dimensional chords
annulus:
  type: fixed_axial_chord
  cx_gap: [0.1, 0.06, 0.1]
  cx_row: [0.1, 0.1]

# Coarse H-mesh
mesh:
  type: h
  yplus: 30.0
  resolution_factor: 0.5

# Define one mid-span section in stator and rotor
blades:
    - spf: 0.5
      thick: [0.04, 0.12, 0.35, 0.2, 0.0, 0.15]
      camber: [0., 0., 0.0]
      theta_offset: 0.1
    - spf: 0.5
      thick: [0.04, 0.12, 0.35, 0.2, 0.0, 0.15]
      camber: [0., 0., 0.0]

# Circulation coefficient to set blade loadings
nblade:
  - Co: 0.6
  - Co: 0.6

# Configure the RANS solver
solver:
  type: ember
  n_step: 2000
  n_step_avg: 1000
  # smooth2_adapt: 0.5

# Configure iterative updates of the geometry
iterate:
  # Make the mean-line loss match CFD
  mean_line:
    tolerance:
      Ys: 0.01
  # Correct for deviation using trailing-edge recamber
  deviation:
  # Correct for incidence using leading-edge recamber
  incidence:

# Additional plots to produce
post_process:
  # Loss at stator and rotor exits
  # Non-dimensional meridional coordinate m is defined:
  #   m=0 at inlet
  #   m=1 at stator LE
  #   m=2 at stator TE,
  #   m=3 at rotor LE
  #   m=4 at rotor TE
  #   m=5 at exit
  - type: contour
    coord: m
    value: [2.48, 2.52]
    variable: Alpha
  - type: contour
    coord: m
    value: [2.48, 2.52]
    variable: Cho
  - type: contour
    coord: m
    value: [2.48, 2.52]
    variable: Ys
  # Mid-span Mach
  - type: contour
    coord: spf
    value: 0.5
    variable: Ma_rel