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In-flight thrust determination for high-bypass-ratio turbofan using residual error methodology

  • Pedro Del Mônaco Monteiro
  • Rafael Mattar Machiaverni
  • Cleverson Bringhenti
  • Jesuino T. Tomita
Technical Paper
  • 45 Downloads

Abstract

Advances in turbofan engine technology have led to engines with growing bypass ratios and lower fan pressure ratios, increasing the complexity of the in-flight thrust determination. Thrust values cannot be directly measured in flight; therefore, ground-level test are carried out, and the results calculated from thermodynamic properties of the gas are compared to the force exerted by the engine on the test bench. The result of this comparison is a scalar that is applied to the fan pressure ratio, fan pressure correlation, which attempts to minimize the error between the measured and calculated values. After the thermodynamic properties of the gas are measured during in-flight tests and together with the fan pressure correlation are used to calculate the in-flight thrust. The calculation procedure is implemented through VISUAL BASIC scripts, in the MICROSOFT EXCEL® environment. These scripts are used to calculate the generated thrust and the mass flow that go through the engine from the thermodynamic properties of the gas obtained from a high-fidelity numerical simulation of this engine. These results are then validated against the thrust and mass flow values calculated by this model. An analysis of the free-stream suppression effects on thrust is carried making use of these scripts.

Keywords

IFTD Propulsion Gas turbine Turbofan Thrust determination 

Abbreviations

ADP

Advanced ducted propulsion

AIR

Aerospace Information Report

ANAC

Agência Nacional da Aviação Civil

ATF

Altitude Test Facility

CFD

Computational fluid dynamics

FAA

Federal Aviation Administration

IFTD

In-flight thrust determination

RERR

Residual error

List of symbols

ρ

Density

A

Area

CD

Flow coefficient

CV

Velocity coefficient

CS

Control surface

FG

Gross thrust

FGfan

Fan gross thrust

FN

Net thrust

FNC

Corrected net thrust

FPC

Fan pressure correlation

FPR

Fan pressure ratio

FRAM

Ram drag

Fscrub

Scrubbing drag

gamma

Specific heat

M

Mach number

n

Normal vector

N1

Low pressure spool rotational speed

NPR

Nozzle pressure ratio

Pt

Total pressure

Pa

Atmospheric pressure

Ps

Static pressure

R

Gas constant

SFC

Specific fuel consumption

Ta

Ambient temperature

Tt

Total temperature

V

Velocity

\(\dot{W}\)

Mass flow

Wf

Fuel flow

Subscript

a

Ambient

amb

Ambient

ref

Reference

0

Upstream

8

Nozzle outlet

13

Bypass nozzle inlet

18

Bypass nozzle outlet

5, 50

Gas generator nozzle inlet

Notes

Acknowledgements

The authors would like to express their gratitude to EMBRAER and ITA for the opportunity to carry out this work. FAPESP, CNPq, CAPES, FINEP are also acknowledged for their support to the Gas Turbine program developed at the ITA’s Turbomachine Departament.

References

  1. 1.
    Santos GD (2001) In-flight thrust determination and uncertainty analysis for turbofan engines. MSc Thesis, Instituto Tecnológico de Aeronáutica, São José dos Campos, BrazilGoogle Scholar
  2. 2.
    Machiaverni RM (2008) Determinação de Tração em Voo através do Método do Erro Eesidual. MSc Thesis in Portuguese, Instituto Tecnológico de Aeronáutica, São José dos Campos, BrazilGoogle Scholar
  3. 3.
    Mattingly JD (2006) Elements of propulsion: gas turbines and rockets. AIAA Education Series, Published by the American Institute of Aeronautics and AstronauticsGoogle Scholar
  4. 4.
    UNITED STATES (1964) FEDERAL AVIATION ADMINISTRATION. Title 14 code of federal regulations—CFR part 25 airworthiness standards: transport category airplanes. Washington, DCGoogle Scholar
  5. 5.
    ANAC BRASIL, AGÊNCIA NACIONAL DA AVIAÇÃO CIVÍL (2014) (RBAC) 25:2014: Regulamento Brasileiro da Aviação Civil, Brasilia, DFGoogle Scholar
  6. 6.
    SOCIETY OF AUTOMOTIVE ENGINEERS SAE International, AIR 5450: advanced ducted propulsor in-flight thrust determination. USA, 2008Google Scholar
  7. 7.
    Monteiro P, Del M (2015) Determinação de Tração em Voo para Motores Turbofan de Alta Razão de Bypass Utilizando o Método do Erro Residual”. MSC Thesis in Portuguese, Instituto Tecnológico de Aeronáutica, São José dos Campos, BrazilGoogle Scholar
  8. 8.
    SOCIETY OF AUTOMOTIVE ENGINEERS (2006) AIR 1703A: In-flight thrust determination. USAGoogle Scholar
  9. 9.
    SOCIETY OF AUTOMOTIVE ENGINEERS (2011) AIR 1678B: uncertainty of in-flight thrust determination. USAGoogle Scholar
  10. 10.
    SOCIETY OF AUTOMOTIVE ENGINEERS (2012) AIR 4065A: propeller/propfan in-flight thrust determination. USAGoogle Scholar
  11. 11.
    Conners TR, Sims RL (1998) Full flight envelope direct thrust measurement on a supersonic aircraft. Washington, DC: NASA, (NASA TM-1998-206560)Google Scholar
  12. 12.
    Niewald PW, Parker SL (1999) Flight test techniques employed to successfully verify F/A-18E in-flight lift and drag. In: AIAA AEROSPACE SCIENCES MEETING AND AND EXHIBIT, 37, Reno (AIAA 99-0768)Google Scholar
  13. 13.
    Köpf FU, Bürklin H, Homeyer C (2002) Method for In-Flight Thrust Determination for Rolls-Royce BR700-715 Turbofan Engines During the Boeing 717-200 Flight-Test”. In: Deutscher Luft und Raumfahrtkongress Lilienthal-Oberth E.V (DGLR-JT2002-204)Google Scholar
  14. 14.
    Blevins J, Wagner D (2000) An uncertainty assessment of thrust determination in altitude ground test facilities”. In: AIAA AEROSPACE SCIENCES MEETING & EXHIBIT, 38, 2000, Reno. (AIAA 2000-0413)Google Scholar
  15. 15.
    Collares RS, Barbosa JR, Parizi-Negrão JR (2000) Uncertainty Analysis in Flight Thrust Determination. In: CONGRESSO BRASILEIRO DE ENGENHARIA E CIÊNCIAS TÉRMICAS (ENCIT), 2000, Porto Alegre, Brazil, Paper S24P08Google Scholar
  16. 16.
    Hoff JC (2007) Toward a stochastic in-flight thrust determination process. In: Congresso SAE BRASIL, 16, 2007, São Paulo. SAE Brasil, 2007. Artigo 2007-01-2542Google Scholar
  17. 17.
    Gould J, McGurgan R (2010) Flying test bed performance testing of high-bypass-ratio turbofans. SAE Int J Aerosp 2(1):67–74.  https://doi.org/10.4271/2009-01-3133 CrossRefGoogle Scholar
  18. 18.
    SOCIETY OF AUTOMOTIVE ENGINEERS (2009) AS 755D: aircraft propulsion system performance station designation and nomenclature. Warrendale, PA, 2009Google Scholar
  19. 19.
    Hill P, Peterson C (1992) Mechanics and thermodynamics of propulsion, 2nd edn. Prentice Hall, USA (S.l.) Google Scholar
  20. 20.
  21. 21.
    NATO, North Atlantic Treaty Organization (2007) Performance prediction and simulation of gas turbine engine operation for aircraft, marine, vehicular, and power generation. RTO Technical Report, TRV-AVT-036Google Scholar
  22. 22.
    Bringhenti C (1999) Análise de desempenho de turbinas a gás em regime permanente, 1999, 228 p. Thesis (M.Sc in Aeronautics and Mechanical Engineering)—Instituto Tecnológico de Aeronáutica, São José dos CamposGoogle Scholar
  23. 23.
    Bringhenti C (2003) Variable geometry gas turbine performance analysis, 2003, 143 p. Thesis (PhD in Aerospace and Mechanical Engineering)—Instituto Tecnológico de Aeronáutica, São José dos CamposGoogle Scholar
  24. 24.
    Silva FJS (2011) Estudo de desempenho de turbinas a gás sob a influência de transitórios da geometria variável. 2011. 133 p. Thesis (Ph.D in Aerospace and Mechanical Engineering)—Instituto Tecnológico de Aeronáutica, São José dos CamposGoogle Scholar
  25. 25.
    Gazzetta JH (2017) Real-time gas turbine generic model for performance simulations. Thesis (PhD in Aerospace and Mechanical Engineering)—Instituto Tecnológico de Aeronáutica, São José dos CamposGoogle Scholar

Copyright information

© The Brazilian Society of Mechanical Sciences and Engineering 2018

Authors and Affiliations

  1. 1.EMBRAER, São José dos CamposSão PauloBrazil
  2. 2.Turbomachines DepartmentAeronautics Institute of Technology (ITA), São José dos CamposSão PauloBrazil

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