# ANSYS CFX 2025 R1 Solver Configuration
# HPT Blade Conjugate Heat Transfer - Cruise Steady-State (COU2)
# ---------------------------------------------------------------
# NOTE: This configuration re-uses COU1 (take-off) model form, mesh,
# turbulence closure, and numerical settings with operating-point changes
# ONLY. See aero-evidence-cou1/cfx_solver_settings.txt for model form.

[General]
Solver                    = ANSYS CFX 2025 R1
Analysis Type             = Steady State
Domain Type               = Rotating frame + solid conduction
Turbulence Model          = SST k-omega
Double Precision          = Yes
Model Version             = HPT-CRUISE-v2.1 (branched from HPT-TOFF-v2.1)

[Engine Operating Point]
Condition                 = Cruise steady-state, FL350, M0.82
Inlet Total Temperature   = 1450 K (profile from engine test Run #63, cruise)
Inlet Total Pressure      = 18.0 bar
Outlet Static Pressure    = 7.8 bar
Rotational Speed          = 10,500 RPM
Cooling Flow Ratio        = 3.5% of mainstream
Reynolds Number (chord)   = 0.85e6 (engine cruise)
Exit Mach Number          = 0.88 (engine cruise)

[Cascade Rig Match - CRITICAL GAP]
Cascade Reynolds Number   = 1.20e6 (used to validate COU1)
Cascade Exit Mach         = 0.92 (used to validate COU1)
Reynolds Delta at Cruise  = (1.20e6 - 0.85e6) / 0.85e6 = +41 percent
                          = Cascade Re is 41% HIGHER than cruise engine Re.
                          = Outside the take-off match envelope (4.8%) for
                          = which the cascade rig was designed.
Mach Delta at Cruise      = (0.92 - 0.88) / 0.88 = +4.5 percent
Temperature Ratio Delta   = Cascade T/T_ref calibrated for take-off (1650K);
                          = cruise operating point has different Tu/T and
                          = different radiation contribution not captured
                          = in cascade.
Rig Representativeness    = NOT representative of cruise. Cascade designed
                          = and instrumented for take-off mid-span only.

[Mesh]
Mesh                      = Inherited from COU1 (6,400,000 cells, mid-span focus)
                          = No re-meshing performed for cruise.
Note                      = COU1 tip region gap also applies to COU2 inheritance.

[Boundary Conditions]
Inlet Type                = Total Temperature + Total Pressure radial profile
                          = from engine test Run #63 (cruise)
Wall Condition            = Conjugate heat transfer (same as COU1)
Rotor-Stator Interface    = Frozen rotor

[Material]
Blade Material            = Inconel 718 (same as COU1, lot MC-2024-0341)
Thermal Conductivity      = Re-evaluated at cruise temperature range
                          = 11.1 W/(m K) at 700K (cruise peak metal)
Specific Heat             = 428 J/(kg K) at cruise temperature
Density                   = 8190 kg/m3

[Convergence]
Residual Target (RMS)     = 1.0e-6 (all equations)
Max Iterations            = 3000
Actual Convergence        = 1847 iterations, residuals 2.1e-7 to 5.4e-7
Numerical Error Estimate  = Bounded within discretization error budget.

[Results Summary - Cruise]
Peak Metal Temperature    = 1063 K (mid-span, pressure side trailing edge)
                          = Acceptance criterion: <= 1080 K. MET.
Creep Damage Accumulation = 0.64 Miner fraction over 25,000 hours
                          = Acceptance criterion: <= 0.70. MET.
