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1Advanced Capabilities For Gas Turbine Engine Performance Simulations

Alexiou, Baalbergen, Kogenhop, Mathioudakis, Arendsen

Laboratory of Thermal Turbomachines

National Technical University of AthensNational Aerospace Laboratory, NLR

The Netherlands

Advanced Capabilities For Gas Turbine Engine

Performance Simulations

A. Alexiou, E.H. Baalbergen,O. Kogenhop, K. Mathioudakis, P. Arendsen

http://www.vivaceproject.com
http://www.vivaceproject.com/http://www.vivaceproject.com/

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Implementing Component Zooming and Distributed Simulations

in PRopulsion Object-Oriented SImulation Software

PROOSIS

Paper Objective & Definitions

Component Zooming: execution of higher order analysis code and

integration of its results back in the 0-D engine cycle

Distributed Simulations: technologies that enable a simulation

program to execute on a computing system containing multipleprocessors interconnected by a communication network

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q PROOSIS OVERVIEW

q Compressor Stage-Stacking

q The Engine Model

q COMPONENT ZOOMING

o The de-coupled Approach

o The semi-coupled Approach

o The fully-coupled Approach

q DISTRIBUTED SIMULATIONS

o Implementing Distributed Simulations

o Prototype Development

o Future Developments

q SUMMARY & CONCLUSIONS

Contents

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PROOSIS OVERVIEW: Code View

Component

Libraries

Library

EL Files

Output Window

Component EL

object-oriented

code containing

mathematical

description of realcomponent

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PROOSIS OVERVIEW: Schematic View

Library

Palette

Drag-and-drop icons

from palette to

construct engine

model.

Connect

components through

appropriate

communication ports

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PROOSIS OVERVIEW: Simulation View

Define

EngineMathematical

Model and

Simulation

Cases

Graphical

representation of

results

Describe in EL

calculation

mode or type

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q PROOSIS OVERVIEW


q The Engine Model

q COMPONENT ZOOMING









Contents

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Compressor Stage-Stacking: Methodology

Calculation of

individual stage exit properties from

dimensionless stage characteristics

and geometry data

stack stages together to evaluate

overall compressor performance

0

2

4

6

8

10

12

14

PressureRatio

10 15 20 25 30

Corrected Mass Flow

IsentropicEfficiencyContours

7000

7500

8000

8500

9000

9500

10

000

10500 1

1085

11750

0 .86

0.85

0.84

0.82

0.80

0.75

0.70

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Compressor Stage-Stacking: Implementation

FORTRAN: SUBROUTINE stageStack (arguments)

compiled as static library (.lib)PROOSIS: FORTRAN FUNCTION stageStack (arguments)

IN stageStack.lib

OR

C++ wrapper for FORTRAN subroutine:

extern "C" void __stdcall STAGESTACK (arguments);void stageStackClass::stageStack(arguments)

{STAGESTACK (arguments); }

PROOSIS: EXTERN CLASS stageStackClass

METHODS

EXTERN METHOD stageStack (arguments)

END CLASS

INCLUDE stageStack.h IN stageStack.lib

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q PROOSIS OVERVIEW


q The Engine Model

q COMPONENT ZOOMING









Contents

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Engine Model

Single-Shaft Industrial Gas Turbine Engine

with 15-stage axial compressor

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Engine Model

Single-Shaft Industrial

Gas Turbine Engine

with 15-stage axial compressor

0

2

4

6

8

10

12

14

PressureRatio

10 15 20 25 30

Corrected Mass Flow

Isentropic EfficiencyContours

7000

7500

8000

8500

9000

9500

1000

0

10500

11085

11750

0.86

0.85

0.84

0.82

0.80

0 .75

0.70

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Component Zooming: Compressor 1-D

GasInGasOut

GasTurbo

AbsCompressor

BETA map

Compressor#SasP

MFT map

Abstract component containing general interface

& equations for standard library components

Abstract component containing general interface

& equations for standard library turbo-components

Abstract component containing core

compressor calculations

AbsCompressor1D

Compressor1D#SasP

Abstract component calling

stage-stacking functionUser-specified

No of bleed ports

User-specified

No of bleed ports

Compressor 1-D Inheritance Tree

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Component Zooming: De-coupled Approach (DCA)

1D

Mass Flow

Pressur

eRatio

Design

Point

Run multi-point

steady-state

simulation

Instantiate

Compressor 1-D

Produce PROOSIS compatible

compressor 1-D map file

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Component Zooming: De-coupled Approach (DCA)

Mass Flow

PressureRa

tio

Design

Point

Run engine simulation using

compressor 1-D map

Select this map

in compressor

Editor

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Component Zooming: Results (DCA)

Mass Flow

PressureRatio

0-D

1-D

Design

Point

Mass Flow

IsentropicEfficiency

0-D1-D

-1.5

-1.1

-0.7

-0.3

0.1

0.5

Load

%

differenceinHeatRateEffect

of

Compressor Zooming

on

Heat Rate vs Load

Characteristic

Comparisonof

0-D & 1-D

Maps

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Component Zooming: Semi-coupled Approach (SCA)

1. Corrected flow zooming scalar2. Isentropic efficiency zooming scalar

3. Fuel flow rate

1. Mass flow error2. Isentropic efficiency error3. Rotational speed

IntrinsicNewton-Raphson

Function

Run Engine Model

All 0-D components

Call External

Compressor Stage-Stacking

Function

Get Compressor 0-D

rotational speed, pressure ratio

Inlet temperature & pressure

Get Compressor 1-D

mass flow and efficiency

Stage geometry

& characteristics

Specified load &

Rotational speed

Independent

Variables

Objective

Variables

PROOSIS

EXPERIMENT

SCHEME

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The meaning of Modification factorsThe meaning of Modification factors

Transformation of component performance maps

PressureRatio

Corrected Mass Flow

q0

q

0q

qf

q=


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Structure of Adaptive modelsStructure of Adaptive models

krefp

kp

kx

x

f,,

,=

Modification factors fkfor components

kp

x,

krefpx ,,

: Actual value for parameter

: Reference value for parameter

Transformation of component performance maps


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0.988

0.992

0.996

1

1.004

1.008

1.012

Load

Scalar

Corrected Mass Flow

Isentropic Efficiency

Component Zooming: Results (SCA)

Variation of Zooming Scalars with Load

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Component Zooming: Fully-coupled Approach (FCA)

TYP MAP

Pt

Cmp1D

Replace Compressor 0-D with 1-D one

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Component Zooming: Results (FCA)

0.583Compressor Power

-0.238Compressor Polytropic Efficiency

0.211Compressor Pressure Ratio

0.438Compressor Delivery Temperature

0.111Compressor Inlet Flow

0.289Fuel Flow Rate

% DIFFERENCEPARAMETER

Design Point Case

1.5% inter-stage bleed from 10th stage

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q PROOSIS OVERVIEW


q The Engine Model

q COMPONENT ZOOMING









Contents

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Distributed Simulations: Rationale & Features

q Collaborative modelling among possibly

geographically dispersed engineers

q Easy and efficient deployment of subsystem models

q Protection of ownership and IPR

qReduction of simulation time through load distribution

q Size and complexity of the simulation model may grow

irrespective of capability of computing infrastructure

q Reuse of submodels in different simulations

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Distributed Simulations: Implementing DS

Technologies considered:

CORBA: complex; did not catch up with growing Web developmentsand demands; high run-time costs; difficulties with security; versions &

difficulties in backward compatibility; not supported by Microsoft...

DCOM: serious security problems; did not catch up with growing Web

developments and demands; deprecated in favour of .NET

Java RMI: Java specific; being obscured by Web Service technology

XML and SOAP: slower than e.g. CORBA and RMI but providing good

basis for secure distributed web-based solutions in wide-area contexts

Web Services: uses open standards and protocols (incl. SOAP and

XML); commonly used nowadays to implement secure distributed

solutions in SOA style; standards and tools are emerging

Web Service: state-of-the-art technology enabling software components(clients, servers) to communicate over a network using standard

messages and formats

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Distributed Simulations: Prototype Development (I)

Prototype in VIVACE context: PROOSIS with compressor

stage stacking function, available as User Library,running on a remote computer

Compressor stage stacking function:

developed by, and proprietary code of NTUA

written in Fortran, available as a shared library (DLL) on

Windows

available to PROOSIS users at NTUA as a PROOSIS

User Library (PROOSIS mechanism to include customer

code in engine simulations) code may be used but cannot be installed outside NTUA

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Distributed Simulations: Prototype Development (II)

Compressor Zooming via

Remote Web Service

Invocation between

NLR & NTUA

PROOSIS simulation inThe Netherlands

Stage Stacking Calculation in

Greece

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Distributed Simulations: Prototype Development (III)

Inte

rnet

Application Server

PROOSIS

Web Service

Operation

Stage-Stacking

Function

Server (NTUA)

PROOSIS

Client (NLR)

PROOSIS

Web

Component

Enables remote use

and sharing of User

Libraries over theInternet without

distributing the code

of the libraries

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Distributed Simulations: Prototype Development (IV)

SOAP overinternet

SOAP over internet

3

PROOSIS WebService

Component

(Java)JNI

IntermediateCode(C++)

Stage-StackingFunction

(FORTRAN)

4

5

PROOSISCustom Library

(C++)

Web ServiceClient(Java)

JNI

1

2

Client Side (NLR) Server Side (NTUA)

Layered Structure of Prototype

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Distributed Simulations: Live Public Demo

NLR

NTUA

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Distributed Simulations: Future Developments

Design of more generic (re-usable) interface

multiple function implementationsnot all layers need to be modified

additional overhead and delays in communication

Reduction of overhead caused by conversions & data transfers

use pure C++ development environment

C++ support for Web Services limited/unstable

Java platform allows integration with other collaborative tools

Reduction of overhead in DLL loading and unloading

load DLLs once and dispose after final calculation

Multi-user and security

Use Web Service Security specification

allow multi-user access

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q PROOSIS OVERVIEW

q Compressor Stage-Stackingq The Engine Model

q COMPONENT ZOOMING









Contents

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Summary & Conclusion (I)

PROOSIS is a standalone, multi-platform, object-oriented

simulation environment for gas turbine engine performancesimulations. It can be used to create, run, manage and share

engine models using either the standard or custom libraries

of engine components. The feasibility of performing multi-

fidelity and distributed simulations with PROOSIS was

demonstrated in this paper.

Using the model of an industrial gas turbine engine and a 1-D

compressor stage stacking code as an example, different

implementations for integrating high fidelity component

analysis in overall engine simulations were presented. The

tools flexible and extensible architecture gives the user thefreedom to select the most suitable approach for a particular

simulation case.

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Summary & Conclusion (II)

The stage stacking code is also used to demonstrate

distributed simulations. A prototype of a Web Component has

been created and successfully tested that remotely invokes

the code from an engine simulation, via the internet, using

Web Services technology.

These demonstrations prove that the tools architecture isadaptable enough to integrate different modelling methods

and its potential to fulfil its role as a shared simulation

environment.

Documents

GT2007-27086-pre