Document
The Computing &
Interdisciplinary Systems
Office
Annual Review and Planning Meeting
October 9-10, 2002
Aircraft Engine Systems
Joseph P. Veres
Computing and Interdisciplinary Systems Office 2002 CISO Review Glenn Research Center
Aircraft Engine Systems
• Organization • Vision and Objective • General Description • Schedule / Milestones • FY02 Accomplishments • FY03 Plans • Technical talks to follow • Summary 2002 CISO Review NASA/TM—2003-211896 73
Organization
Office of Aerospace Technology (Code R) Dr. Jerry Creedon, Associate Administrator (HQ) Revolutionize Aviation Theme Area Terry Hertz, Program Director (HQ) Vehicle Systems Program Level 1 Richard Wlezien (HQ) Aerospace Propulsion and Power Program Level 2 Dr. Gary Seng (NASA GRC) Propulsion Fundamental Research Project Level 3 Pete McCallum (NASA GRC) Turbine Engine Simulation Level 4 Joe Veres (NASA GRC) 2002 CISO Review
Aircraft Engine Systems
Vision and Objective The objective is to develop the capability to numerically model the performance of gas turbine engines used for aircraft propulsion. This capability will provide turbine engine designers with a means of accurately predicting the performance of new engines in a system environment prior to building and testing. The 'numerical test cell' developed under this project will reduce the number of component and engine tests required during development. As a result, the project will help to reduce the design cycle time and cost of gas turbine engines.
This capability will be distributed to U.S. turbine engine manufacturers and air framers. This project focuses on goals of maintaining U.S.
superiority in commercial gas turbine engine development for the aeronautics industry.
2002 CISO Review NASA/TM—2003-211896 74
Aircraft Engine Systems
General Description This project will develop computer modeling and simulation capabilities that are of long-term strategic importance to future subsonic and supersonic propulsion. This research is mainly computational and aimed at developing modeling capabilities that could offer significant reductions in design and development cost of next generation subsonic and supersonic propulsion systems. This will enable the designers of new engines to use physics-based predictions of engine performance early in the design process. The Navier- Stokes flow simulations will enable detailed modeling of component aerodynamic interaction effects on engine performance. Key unknowns will be predicted such as radial profiles of flow conditions at component boundaries that are typically unknown to the designer until after the first engine is built and tested. Multi-disciplinary interaction effects on engine performance will also be modeled. This will help to reduce the reliance on component test data and also reduce the number of engine design-build-test iterations.
2002 CISO Review
Aircraft Engine Systems
Schedule / Milestones FY02 FY03 FY04 FY05 3-D Turbofan Engine Simulation 1 3 4 6 2 5 CIAPP Cycle Code Development 1. 3-D flow simulation of an aircraft turbofan engine in under 15 hours of CPU wall clock time using APNASA turbomachinery code and the National Combustion Code (NCC) 2. CIAPP cycle code enhanced with a Visual Based Syntax assembly of complete engine 3. Demonstrate CIAPP V2.0 to automate zooming to the 3-D steady-state aero-thermal engine simulation 4. Demonstrate prototype of a 3-D unsteady turbomachinery simulation in turbofan engine 5. Demonstrate prototype "intelligent engine" using CIAPP cycle code coupled to controls code 6. Demonstrate prototype of a 3-D multidisciplinary simulation in turbofan engine 7. Demonstrate CIAPP V3.0 to automate zooming for 0-D to 3-D multi-disciplinary engine simulation using APNASA / NCC and structural / thermal codes 2002 CISO Review NASA/TM—2003-211896 75
Aircraft Engine Systems
FY02 Accomplishments • 3-D flow simulation of the GE90 turbofan engine has been successfully run in under 15 hours of CPU wall clock time using the APNASA and NCC codes. This was a Strategic Implementation Plan (SIP) fiscal year 2002 milestone for NASA GRC (01A6.1).
• CIAPP V1.5 thermodynamic cycle code has been enhanced with a Visual Based Syntax assembly of complete engine.
Phase 3 Meeting was held on March 13, 2002. The results were presented in the area of high fidelity simulations and lessons learned from coupling of high fidelity and multi-disciplinary codes.
2002 CISO Review
Aircraft Engine Systems
FY02 Accomplishments (continued) GE90 Turbofan Engine Simulation in under 15 hours of CPU wall clock time 2002 CISO Review NASA/TM—2003-211896 76
Aircraft Engine Systems
FY03 Plans Demonstrate CIAPP V2.0 to automate zooming to the 3-D steady-state aero-thermal engine simulation of the GE90 turbofan engine.
The CIAPP V2.0 code and the 3-D engine component simulations with APNASA and NCC will generate “mini maps” around the operating point of interest for the engine components. These maps will be passed back to the CIAPP thermodynamic cycle code, which will then be run to convergence ( see flow chart next page ).
2002 CISO Review
Aircraft Engine Systems
FY03 Plans (continued) Iteration (n) Iteration (n+1) The engine cycle code (CIAPP V2.0) will be The engine cycle engine cycle run at the operating point of interest using run with new ‘initial guess’ component maps ‘mini-maps’ boundary conditions Cycle will generate 0-D BC’s for the fan, LP Cycle generate for 3-D simulations and HP compressors, combustor and LP and new 0-D BC’s HP turbines.
CIAPP V2.0 spawn CIAPP V2.0 will spawn execution of 3-D 3-D simulations execution of 3-D component simulations (fixed inlet profiles) simulations with real inlet radial profiles 3-D simulations will create ‘mini maps’ ‘mini maps’ for cycle around operating point of interest, and pass the maps to the cycle code 2002 CISO Review NASA/TM—2003-211896 77
Aircraft Engine Systems
Technical talks to follow: “ High Fidelity Simulation of the GE90 Turbofan Engine” Mark G. Turner ( AP Solutions / University of Cincinnati) “NCC Simulation of the GE90 Combustor” Andrew Norris (OAI) Engine Simulation Team Mark G. Turner Compressor and turbine simulations with APNASA Rob Ryder Combustion simulations with NCC, grid generation Andrew Norris Combustion simulations with NCC, code coupling John Adamczyk APNASA turbomachinery flow code Nan-Suey Liu National Combustion Code (NCC) John Gallagher Combustor CAD geometry John Reed Thermodynamic cycle of GE90 engine with CIAPP Scott Townsend Code coupling toolkit development Bill Pavlik CIAPP engine cycle model 2002 CISO Review
Aircraft Engine Systems
Summary The GRC SIP Milestone number 01A6.1 has been successfully achieved in FY02. The title of the milestone is: “Turbofan Flow Path Simulation” The full primary flow path simulation of a modern two spool turbofan engine has been achieved running on hundreds of processors in less than 15 hours of CPU wall clock time.
A paper have been presented at the 2002 Joint Propulsion Conference titled: “High Fidelity 3D Turbofan Engine Simulation with Emphasis on Turbomachinery-Combustor Coupling”, AIAA-2002-3769 2002 CISO Review NASA/TM—2003-211896 78