Welcome to the AA 461 Airbreathing Propulsion Project for the Winter Quarter 2024. This project focuses on the design of a gas turbine engine core, comprising the compressor, combustor, and turbine components, to meet specific performance, cost-efficiency, and design considerations.
The objective of the project is to design a gas turbine engine core that optimizes performance, maintains acceptable turbine inlet temperatures, identifies cost-efficient design solutions, and handles specified mass flow at designated inlet conditions.
Teams Each Project Team is composed of two students. Please email JCH by Wednesday, February 14, with your proposed team.
Utilize existing software for the analysis of the compressor, combustor, and turbine. The software (EOP2) can be found online at EOP2 Software. Utilize COMPR and TURBN programs for compressor and turbine performance analysis, respectively. The CEARUN program can be employed for combustion analysis.
Prepare a concise written report summarizing your work. The report should include a problem statement, approach, inputs used, selected design point rationale, description of key non-software steps, performance plots, and a proposed configuration sketch. Aim for a report length of approximately 8 pages, including figures.
The Project contributes up to 40 Homework points for each team member. Project Reports are due on Friday, March 1.
Given Conditions
- Inlet total temperature: 298 K
- Inlet total pressure: 101.3 kPa
- Mass flow rate: 60 kg/s
- Rotor angular velocity: 1000 rad/s
- Polytopic efficiency: 0.9
- Specific heat ratio: 1.4
Variables
- Number of stages
- Swirl distribution and α1
- Solidity
Considerations
- Compressor pressure ratio optimization
- Work required to run the compressor
- Compressor efficiency
Given Conditions
- Inlet conditions: Compressor outlet
- Adiabatic T and composition at constant p
Variables
- Fuel type
- Combustion strategy
Considerations
- Combustor exit/turbine entrance temperature
- Estimates of exhaust emissions
- Given Conditions
- Inlet conditions: Combustor output
- Loss model: Polytropic efficiency
- Specific heat ratio: 1.3
Variables
- Number of stages
- Mass flow rate
- α1 (first stage)
Considerations
- Minimize turbine stages for cost efficiency
- Turbine efficiency
- Mass flow rate considerations
- Pressure and temperature changes across compressor and turbine stages
- Combustor product temperature vs. stoichiometry
- Compressor and turbine efficiencies
- Work/power required to drive compressor and produced by turbine
The AA 461 Airbreathing Propulsion Project offers a comprehensive exploration of gas turbine engine core design principles and considerations. Through collaborative effort and rigorous analysis, teams aim to develop innovative solutions meeting performance and cost-efficiency criteria.