Passage flow & aerodynamic loading
Resolve pressure gradients, wakes, secondary flows, separation, incidence effects and passage-to-passage behaviour.
GAS TURBINE & TURBOMACHINERY CFD
Resolve rotating-flow, cooling and blade-passage questions with a practical CFD methodology.
Abecator supports turbomachinery and gas-turbine CFD where rotating interfaces, near-wall resolution, secondary flow, cooling and thermal effects must work together to answer an engineering question.
ENGINEERING PROBLEMS
Application-level support for rotating machinery CFD.
Useful turbomachinery CFD depends on consistent reference frames, interfaces, periodicity, boundary conditions and a mesh that respects the dominant flow structures.
Rotating domains & interfaces
Review rotating frames, sliding or mixing interfaces, periodicity and frame-consistent boundary conditions.
Cooling & secondary airflow
Assess cooling passages, flow splits, leakage paths, pressure margins, heat transfer and local near-wall behaviour.
Thermal-fluid interaction
Connect hot-gas-path flow, cooling effectiveness, wall heat flux and component thermal response when CHT is required.
TYPICAL CFD SCOPE
Build the model around the turbomachinery question.
The right scope may be a single passage, periodic sector, full annulus, isolated cooling feature or focused review of an existing model.
01
Define operating point
Mass flow, pressure ratio, speed, temperatures, inlet profiles and the performance quantity or local physics to predict.
02
Choose domain & interfaces
Reference frames, periodicity, rotating/stationary coupling and the minimum domain that preserves the required physics.
03
Design the mesh
Near-wall resolution, leading/trailing edges, tip gaps, cooling holes, wakes and interface quality receive targeted refinement.
04
Verify performance & local flow
Check balances, pressure/temperature trends, wall quantities, sensitivity and whether the result supports the engineering decision.
WHAT GETS CHECKED
Common failure points in turbomachinery CFD.
Many issues arise from setup consistency rather than turbulence modelling alone.
A✓
Frame and boundary consistency
Velocity definitions, total/static quantities and rotating/stationary reference frames must be physically consistent.
B✓
Mesh around critical features
Leading edges, trailing edges, tip gaps, cooling holes, wakes and boundary layers are checked for adequate resolution.
C✓
Interface behaviour
Flux transfer, interpolation quality, periodicity and rotating-interface choices are reviewed against the intended fidelity.
D✓
Performance and conservation
Mass, energy, pressure ratio, losses and local flow structures are checked together before conclusions are drawn.
POSSIBLE DELIVERABLES
From focused model review to developed turbomachinery workflows.
Scope can focus on setup risk, a specific flow feature, cooling performance or a repeatable analysis process.
Independent setup review
Check domain strategy, interfaces, mesh, wall treatment, operating conditions, monitors and result credibility.
Turbomachinery CFD methodology
Define a defensible workflow for recurring blade-row, cooling or rotating-machinery studies.
Flow & thermal interpretation
Explain losses, recirculation, pressure fields, cooling distribution, heat transfer and sensitivity relevant to the design question.
Verification plan
Identify the mesh, convergence and sensitivity evidence needed before performance differences are trusted.
SOFTWARE & METHODS
Built around industrial CFD workflows.
Typical methods may include STAR-CCM+, OpenFOAM, rotating reference frames, periodic sectors, steady or transient RANS, CHT, advanced prism layers and application-specific post-processing.
HAVE A TURBOMACHINERY CFD PROBLEM?
Start with the machine, operating point and quantity you need to predict.
Use the project inquiry to describe your geometry/model status, rotating setup, current problem and desired engineering outcome.
ROTATING-FLOW RESOURCES
Check interface and mesh risks before expanding the turbomachinery model.
Rotating-frame choice, interface treatment, near-wall resolution and timestep can dominate the credibility of rotor-stator and blade-passage results.