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Developing advanced Engine Multi-disciplinary Optimization Simulations (DEMOS)

Periodic Reporting for period 3 - DEMOS (Developing advanced Engine Multi-disciplinary Optimization Simulations (DEMOS))

Periodo di rendicontazione: 2019-01-01 al 2019-12-31

What is the problem/issue being addressed?

Project DEMOS aims to address the challenges of developing advanced predictive modelling and simulation capabilities for engine design space exploration and performance optimisation of novel propulsion systems such as GOR (Geared Open Rotor) and UBGF (Ultra-high Bypass ratio Geared turboFan). The development of these simulation technologies and the optimization of these advanced powerplant solutions will contribute towards achieving a significant gain in aircraft performance in line with the near term ACARE 2020 targets and future planning towards SRIA 2050 goals.

Why is it important for society?

Project DEMOS will support and enable further development/optimisation of innovative propulsion system configurations with the potential to fulfil the SRIA key challenges. These challenges relate to European industrial leadership, energy supply prioritizing research and reducing the environmental impact while meeting the impact of market needs and flight safety requirements. The targeted outcomes of Project DEMOS can therefore be related to specific SRIA challenges with specific and measurable objectives.

What are the overall objectives?

The aim of Project DEMOS is to develop a flexible and extensible modular multi-disciplinary framework and undertake design space exploration and multidisciplinary optimisation assessments of novel ultra-high bypass and open rotor propulsion concepts at aircraft mission level. The framework comprises two main elements, PRopulsion Object Oriented SImulation Software (PROOSIS) and a customised Technoeconomic Environmental Risk Assessment Framework (TERA2050).
PROOSIS comprises engine and aircraft performance simulation modelling capabilities for mission level assessments. Additionally, development of advanced solvers, numerical methods and engine transient performance modelling capabilities are being undertaken.
PROOSIS will subsequently be integrated with the TERA 2050 framework (in a commercially available integration and optimisation framework). The TERA 2050 framework will comprise an engine preliminary design and weight estimation model, a lifing model and a direct operating cost model.
The main actions and outcomes from the work carried out during this reporting period are:
- Released a new version of PROOSIS in December 2016 with new modelling and simulation capabilities for modelling the performance of advanced engine architectures such as the Ultra-high Bypass Geared Fan (UBGF) and the Geared Open Rotor (GOR).
- Extended component models with aerodynamic design, weight estimation and flow path sizing functionalities.
- Aligned modelling methodologies between UBGF and GOR component models and generated multi-disciplinary PROOSIS engine models.
- Performed parametric multi-point design runs accounting for performance/aerodynamic/structural requirements and constraints at different operating points.
- Carried out preliminary literature review of state-of-the-art lifing methodologies and integrated HPT blade lifing calculations in PROOSIS.
- Carried out a literature review of state-of-the-art lifing methodologies for the HPT and reported the findings in Deliverable 6.1
- Organized Project Annual Review and PROOSIS modelling workshop and performed live demonstration of capabilities developed to Topic Manager.
- Performed UBGF installed engine performance parametric studies accounting for engine weight and drag.
- Compiled and submitted technical paper for UBGF describing capabilities developed and initial results obtained.
- Compiled and submitted technical paper describing a methodology used to predict HPT life.
- NTUA and CU have developed in PROOSIS new component models for the Ultra-high Bypass ratio Geared Fan and the contra-rotating Geared Open Rotor engine configurations
- The functionality of the turbomachinery component performance models was extended with aerodynamic design capabilities through different methodologies ranging in complexity
- An advanced simulation process was then set up in PROOSIS to enable the design of an engine that meets the requirements and constraints over a number of operating points
- Parametric studies were then performed in order to generate the design
- NTUA has developed modelling capabilities to enable transient simulations of advanced aero-engine gas turbines integrated with a control system
- The developed functionalities are demonstrated through simulation of different transient manoeuvres for both conventional and advanced engine configurations
- EAI implemented several mechanisms to perform real-time simulations of the various engine configurations in PROOSIS
- The fidelity of the aircraft performance was approved by the Topic Manager, before actual coupling of the engine performance models and aircraft performance models was undertaken for both the UBGF and GOR engine configurations
- The framework developed to perform sensitivity analysis for the GOR engine was produced and the impact of some key engine cycle parameters at aircraft mission level was shown for the UBGF engine architecture
- The study also accounted for benefits in wing aerodynamics due to rear-mounting of the GOR estimating the reduction in drag produced by the wing was to be 8%
- The payload range analysis clearly indicated a significant and expected reduction (>30%) in mission fuel burn
- NTUA has developed and demonstrated an optimization framework for multi-disciplinary engine design assessments of the UBGF configuration at aircraft mission level
- The framework comprises the multi-disciplinary, multi-point engine design capability developed in WP3 for UBGF coupled with off-design engine performance, aircraft performance and mission analysis
- Based on the technology level assumptions made and the constraints imposed in the design, fuel burn reduction (and therefore CO2 emissions) in excess of 18% are anticipated, compared to conventional EIS2000 engines
- CU covered the different failure modes affecting the hot areas of modern aero-engines such as the GOR and UBGF
- The steps that need to be followed to estimate the life of the HPT discs and blades were detailed: estimation of applied stresses, modelling of the effects of the failure modes, adoption of the failure criteria, and definition of a damage rule
- CU integrated the life estimation models in the DEMOS TERA2025 framework
- WP7 was focussed on utilising established methods to assess the sensitivity of the DOC to key influencing parameters (acquisition price and maintenance costs) and then established viable bounds for them within which the technology would be economically competitive
The new capabilities developed within the first period of DEMOS project constitute a step forward with respect to existing state-of-the-art solutions for overall performance assessment and optimisation of propulsion systems. The proposed solution for robust and flexible multi-disciplinary, multi-point design of conventional and advanced propulsion systems can help reduce analysis time and costs at a preliminary design phase.
Generl layout of PROOSIS Simulation tool
Graphical monitor of PROOSIS
UBGF PROOSIS Schematic Model
Parametric study results
SFC vs. TET vs Altitude
GOR PROOSIS Schematic model
Calculated UBGF Gas Path Geometry for different Fan Pressure Ratio Values