# ANSYS CFX 2025 R1 Solver Configuration
# HPT Blade Conjugate Heat Transfer - Take-off Transient (COU1)
# --------------------------------------------------------------

[General]
Solver                    = ANSYS CFX 2025 R1
Analysis Type             = Steady State (frozen transient point at t=22s, peak TIT)
Domain Type               = Rotating frame + solid conduction
Turbulence Model          = SST k-omega
Double Precision          = Yes

[Engine Operating Point]
Condition                 = Take-off, sea-level static, hot day (ISA+15)
Inlet Total Temperature   = 1650 K (profile from Run #47)
Inlet Total Pressure      = 28.5 bar
Outlet Static Pressure    = 12.3 bar
Rotational Speed          = 13,500 RPM
Cooling Flow Ratio        = 4.2% of mainstream
Reynolds Number (chord)   = 1.26e6 (engine)
Exit Mach Number          = 0.94 (engine)

[Cascade Rig Match]
Cascade Reynolds Number   = 1.20e6 (4.8% below engine)
Cascade Exit Mach         = 0.92 (2.1% below engine)
Temperature Match         = Scaled (Tu/T_freestream preserved, absolute T reduced)
Rig Representativeness    = Mid-span take-off conditions ONLY
                          = Cascade NOT validated for cruise, tip, or off-design

[Mesh]
Mesh Generator            = ANSYS Meshing
Element Type              = Hex-dominant with prism layers
Prism Layers              = 20
First Layer Height (mm)   = 0.002
Growth Ratio              = 1.15
y+ Target                 = < 1.0
Production Mesh (mid-span)= 6,400,000 cells
Tip Gap Mesh              = Coarse (NOT converged) - see mesh_convergence_study.csv

[Grid Refinement Study]
Coarse                    = 1,600,000 cells
Medium                    = 3,200,000 cells
Fine (production)         = 6,400,000 cells
Refinement Ratio (r)      = 1.26 (cbrt(2))
Note                      = r below Celik et al. 2008 / Roache recommended r>=1.3
                          = GCI computed per ASME V&V 20-2009; known underestimate
                          = at r=1.26. Board reviewed; accepted with caveat.

[Boundary Conditions]
Inlet Type                = Total Temperature + Total Pressure radial profile
Wall Condition            = Conjugate heat transfer (partitioned, 1-equation coupling)
Rotor-Stator Interface    = Frozen rotor (suitable for steady analysis)

[Material]
Blade Material            = Inconel 718 (per vendor certificate, lot MC-2024-0341)
Thermal Conductivity      = 11.4 W/(m K) at 800K (MMPDS-18 Table 6.3.1.1.1)
Specific Heat             = 435 J/(kg K)
Density                   = 8190 kg/m3

[Convergence]
Residual Target (RMS)     = 1.0e-6 (all equations)
Max Iterations            = 3000
Actual Convergence        = 2341 iterations, residuals 4.2e-7 to 8.8e-7
Monitor Points            = Peak temp, Cooling effectiveness, Pressure ratio
Numerical Error Estimate  = Bounded within discretization error budget via residual
                          = history and double precision arithmetic (per NASA-STD-7009B
                          = Factor 5.1.2 justification for partial assessment).
