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Supercomputing Nov 4-10, 2000
NASA Glenn Power Grid Challenge

Picture of a Computer Network Diagram and Three Users; Huge Memory, Just Results, and High Speed
The Multifidelity Engine Model consists of CORBA analysis elements that simulate the high-pressure compressor/combustor/turbine subsystem coupled with the low-pressure compressor/turbine subsystem of a turbine engine.
The purpose of this simulation is to determine at what RPM the low- and high-pressure subsystems of the Energy Efficient Engine are balanced. The simulation consists of:
  • A CORBA client program written in Java, which provides the GUI and simulation driver.

  • NPSS CORBA analysis elements:

    LPC
    An instance of ADPAC (a parallel 3D CFD code) configured for the front end (inlet, nacelle, fan, booster, and bypass duct) of the low pressure subsystem as well as external flow.

    HPC
    An instance of ADPAC configured for the high pressure compressor.

    Burner
    An instance of NPSS v1 configured to model the combustor.

    HPT
    An instance of ADPAC configured for the high pressure turbine.

    LPT
    An instance of ADPAC configured for the back end (turbine, mixer, and nozzle) of the low pressure subsystem.

  • NPSS CORBA fluid-fluid interpolator elements which couple between the various instances of ADPAC.
During the simulation the Burner element computes a new HPT inlet flow based on the HPC exit flow and the combustor model. This 0D HPT inlet flow data is then copied to the HPT element. This constitutes a "swap." Next, a selected number of coupled ADPAC iterations are performed to get the coupled simulations to settle to this new set of conditions.

After a selected number swaps between the Burner and other elements, the calculated LP and HP net horsepower values are compared against the maximum allowable imbalance value. If necessary, new estimated shaft RPM values are calculated, and another trial begins.

The simulation terminates when the shaft powers are balanced

Curator: Ryan Spaulding
Last Update: September 25, 2002
NASA Official: Steve Walworth