Helicopter Engine Optimization for Minimum Mission Fuel Burn
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Helicopter Engine Optimization for Minimum Mission Fuel Burn Alexiou, Pons, Cobas, Mathioudakis & Aretakis. Laboratory of Thermal Turbomachines National Technical University of Athens. Acknowledgements. C ollaborative & R obust E ngineering using

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Helicopter Engine Optimization for Minimum Mission Fuel Burn

Alexiou, Pons, Cobas, Mathioudakis & Aretakis

Laboratory of Thermal Turbomachines

National Technical University of Athens


Acknowledgements
Acknowledgements

Collaborative & Robust Engineering using

Simulation Capability Enabling Next Design Optimisation


Contents
Contents

  • INTRODUCTION

  • MODELLING ASPECTS

    • Simulation Environment

    • Engine Performance Model

    • Helicopter Performance Model

    • Mission Analysis

  • OPTIMIZATION METHODOLOGY

  • RESULTS

  • SUMMARY & CONCLUSIONS


Introduction
Introduction

Fuel Impact On Operating Costs

(http://www.iata.org/pressroom/facts_figures/fact_sheets/pages/fuel.aspx)


Introduction1
Introduction

Global Man-Made CO2 Emissions

(ACARE Beyond Vision 2020)


Introduction2
Introduction

Helicopter Uses


Introduction3
Introduction

  • Before this Work

  • Trajectory optimization of helicopter for minimum mission fuel burn

  • Objective of this work

  • To develop a generic methodology suitable for the preliminary engine design phase of optimizing a helicopter engine for minimum mission fuel burn

  • Requirements

  • Helicopter and engine performance models

  • Mission analysis capability


Contents1
Contents

  • INTRODUCTION

  • MODELLING ASPECTS

    • Simulation Environment

    • Engine Performance Model

    • Helicopter Performance Model

    • Mission Analysis

  • OPTIMIZATION METHODOLOGY

  • RESULTS

  • SUMMARY & CONCLUSIONS


Simulation platform
Simulation Platform

PROOSIS (PRopulsion Object-Oriented SImulation Software)

  • Object-Oriented

  • Steady State

  • Transient

  • Mixed-Fidelity

  • Multi-Disciplinary

  • Distributed

  • Multi-point Design

  • Off-Design

  • Test Analysis

  • Diagnostics

  • Sensitivity

  • Optimisation

  • Deck Generation


Simulation platform1
Simulation Platform

  • TURBO library of gas turbine components

  • Industry-accepted performance modelling techniques

  • Respects international standards in nomenclature, interface & OO programming


Engine performance
Engine Performance

Take-off power rating (design point) at sea-level standard conditions



Helicopter performance
Helicopter Performance

  • Total helicopter power

  • Main rotor power

    • Induced

    • Profile

    • Fuselage

    • Potential energy change

  • Tail rotor power

  • Customer power extraction

  • Gearbox power losses



Helicopter performance2
Helicopter Performance

MTOW / SL / STD

SR = Vx / Wfuel


Mission fuel calculation

1800

1600

1400

1200

1000

Altitude [m]

800

600

400

200

0

0

10

20

30

40

50

-200

Time (min)

Mission Fuel Calculation

Mission definition

H/C Specification

e.g. velocity, time for each segment

  • Take-Off weight

  • air bleed/power off-take

2

Air Intake losses

Exhaust losses

1

H/C PERFORMANCE MODEL

MISSION PROFILE

H/C operating conditions

3

H/C new

weight

4

6

7

ENGINE PERFORMANCE MODEL

H/C requirements

(power, air cabin off take, Nrotor)

Fuel Flow Rate

5

Mission Fuel


Mission definition
Mission Definition

Cruise with Vbr for 400 km

Descent

with 12.5 m/s

Climb to 1000m

with Vbe & Vz,max


Contents2
Contents

  • INTRODUCTION

  • MODELLING ASPECTS

    • Simulation Environment

    • Engine Performance Model

    • Helicopter Performance Model

    • Mission Analysis

  • OPTIMIZATION METHODOLOGY

  • RESULTS

  • SUMMARY & CONCLUSIONS


Optimization methodology
Optimization Methodology

-30% < W2 < 30%,

-30% < P22Q2 < 50%

-20% < P3Q24 < 100%

Optimization parameters & their range

Assumed variation of compressor & turbine efficiency and engine weight with change in W2

Variation of turbine cooling flows with Tt41


Optimization calculation flow chart
Optimization Calculation: Flow Chart

Establish baseline engine design and helicopter mission


Contents3
Contents

  • INTRODUCTION

  • MODELLING ASPECTS

    • Simulation Environment

    • Engine Performance Model

    • Helicopter Performance Model

    • Mission Analysis

  • OPTIMIZATION METHODOLOGY

  • RESULTS

  • SUMMARY & CONCLUSIONS



Sfc w2 vs p3q24
ΔSFC & ΔW2 vs ΔP3Q24





Contents4
Contents

  • INTRODUCTION

  • MODELLING ASPECTS

    • Simulation Environment

    • Engine Performance Model

    • Helicopter Performance Model

    • Mission Analysis

  • OPTIMIZATION METHODOLOGY

  • RESULTS

  • SUMMARY & CONCLUSIONS


Summary conclusions
Summary & Conclusions

  • A procedure has been proposed that allows the designer to optimize the engine cycle for minimum fuel burn of a helicopter mission. The approach takes into account changes in the turbomachinery component efficiencies and engine weight due to engine inlet flow rate changes. Limits are imposed for turbine rotor inlet temperature, surge margin and pressure ratio. Turbine cooling/sealing flows are established according to the turbine rotor inlet temperature.

  • For the specific engine-helicopter-mission combination, the total fuel burn benefit ranged from 5.8% to 9.4%, depending on the maximum value of turbine rotor inlet temperature that can be tolerated.

  • The proposed approach is generic allowing the optimization of the engine as well as the helicopter for different combinations of engines and helicopters and different missions or combinations of missions and according to the objectives and limitations set by the designer.


THANK YOU

Laboratory of Thermal Turbomachines

National Technical University of Athens


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