Run time Assessment for Gas Turbine Performance Simulation

Gazzetta Junior, Henrique; Bringhenti, Cleverson; Barbosa, João Roberto; Tomita, Jesuíno Takashi

doi:10.5028/jatm.v10.692

Henrique Gazzetta JuniorCorrespondence author: Henrique Gazzetta Junior | Avenida Cassiano Ricardo, 1.411 - Apto. 84B | CEP: 12.240-540 - São José dos Campos/SP - Brazil | E-mail: henrique.gazzetta@gmail.com

Empresa Brasileira de Aeronáutica - São José dos Campos/SP - Brazil.

https://orcid.org/0000-0001-9454-476X

Cleverson Bringhenti

Departamento de Ciência e Tecnologia Aeroespacial - Instituto Tecnológico de Aeronáutica - Divisão de Engenharia Aeronáutica e Mecânica - São José dos Campos/SP - Brazil.

https://orcid.org/0000-0001-7634-1352

João Roberto Barbosa

Departamento de Ciência e Tecnologia Aeroespacial - Instituto Tecnológico de Aeronáutica - Divisão de Engenharia Aeronáutica e Mecânica - São José dos Campos/SP - Brazil.

https://orcid.org/0000-0001-8912-6045

Jesuíno Takashi Tomita

Departamento de Ciência e Tecnologia Aeroespacial - Instituto Tecnológico de Aeronáutica - Divisão de Engenharia Aeronáutica e Mecânica - São José dos Campos/SP - Brazil.

https://orcid.org/0000-0001-9528-201X

Correspondence author: Henrique Gazzetta Junior | Avenida Cassiano Ricardo, 1.411 - Apto. 84B | CEP: 12.240-540 - São José dos Campos/SP - Brazil | E-mail: henrique.gazzetta@gmail.com

Section Editor: Dimitrios Pavlou

AUTHOR'S CONTRIBUTION

Conceptualization, Gazzetta Junior H, Bringhenti C, Barbosa JR and Tomita JT; Methodology, Gazzetta Junior H, Bringhenti C and Barbosa JR; Investigation, Gazzetta Junior H; Writing - Original Draft, Gazzetta Junior H; Writing - Review & Editing, Gazzetta Junior H; Supervision, Bringhenti C and Barbosa JR.

Simulation module	Input data required
Ambient condition	Ambient static pressure and temperature Flight Mach number Humidity
Air intake losses	Pressure recovery factor
Turbomachine	Inlet mass flow Bypass ratio Shafts efficiencies and power extractions Combustion chamber exit temperature Fuel air ratio in the combustion chamber (lean, rich or stoichiometric) For each compressor: pressure ratio, isentropic efficiency and surge margin For each turbine: isentropic efficiency For the combustion chamber: exit temperature, pressure ratio and isentropic efficiency
Fuel	Lower heating value Hydrogen/carbon ratio
Propelling nozzle	Geometry (convergent or con-di nozzle) Discharge and velocity coefficients (CD and CV)

Relative corrected spool speed (N/N @ Design Point)	Relative corrected mass flow (WR1 @ Design Point)
0.30	0.4151	0.3405	0.2843	0.2270	0.1472
0.40	0.4888	0.4315	0.3569	0.3129	0.2669
0.50	0.5685	0.5286	0.4427	0.4090	0.3640
0.60	0.6534	0.6104	0.5337	0.4714	0.4540
0.70	0.7495	0.7168	0.6933	0.6534	0.5838
0.80	0.8517	0.8272	0.8119	0.7638	0.6933
0.90	0.9652	0.9540	0.9427	0.8681	0.8078
1.00	1.0798	1.0787	1.0511	1.0000	0.9427
1.10	1.1933	1.1933	1.1902	1.1646	1.1186
1.20	1.2781	1.2781	1.2781	1.2771	1.2556

Relative corrected spool speed (N/N @ Design Point)	Compressor pressure ratio
0.30	1.000	1.0420	1.0576	1.0672	1.0720
0.40	1.000	1.0600	1.1128	1.1380	1.1500
0.50	1.000	1.0760	1.1740	1.1980	1.2220
0.60	1.000	1.1320	1.2400	1.2844	1.2980
0.70	1.000	1.2220	1.2760	1.3360	1.4008
0.80	1.000	1.3000	1.3420	1.4296	1.4980
0.90	1.000	1.3288	1.3900	1.5424	1.6000
1.00	1.000	1.3312	1.5100	1.6420	1.7200
1.10	1.000	1.4860	1.6720	1.8004	1.8760
1.20	1.000	1.4680	1.7200	1.8700	1.9900

Relative corrected spool speed (N/N @ Design Point)	Compressor pressure ratio
0.30	0.7559	0.7665	0.7559	0.7251	0.6415
0.40	0.7559	0.7920	0.8026	0.7762	0.7401
0.50	0.7506	0.8026	0.8439	0.8281	0.7762
0.60	0.7454	0.8281	0.8800	0.8281	0.8078
0.70	0.7251	0.8545	0.8800	0.9011	0.8272
0.80	0.6882	0.8545	0.8800	0.9011	0.8272
0.90	0.6415	0.8281	0.8589	0.8800	0.8175
1.00	0.6002	0.7762	0.8589	0.8589	0.7867
1.10	0.5694	0.7762	0.8078	0.7762	0.7251
1.20	0.5174	0.7251	0.7612	0.7762	0.6415

Simulation key inputs	Input values range
Altitude	From sea level up to 15,000 m in steps of 500 m
Mach number	From static up to 0.8 in steps of 0.05
Delta from standard day	From -30 ºC up to +30 ºC in step of 5 ºC
Burner exit temperature	From 1800 K down to 1000 K in steps of 100 K

Name	Solver	Map type
Tab-NRaphson	Newton-Raphson	Tabulated
Tab-Broyden	Broyden	Tabulated
EQ-NRaphson	Newton-Raphson	Equation
EQ-Broyden	Broyden	Equation

\{\begin{matrix} \frac{WF}{{WF}_{Tgt}} - 1 = 0 \\ \frac{FN}{{FN}_{Tgt}} - 1 = 0 \\ \frac{T 4}{T 4_{Tgt}} - 1 = 0 \\ \frac{N 1}{N 1_{Tgt}} - 1 = 0 \\ \frac{N 2}{N 2_{Tgt}} - 1 = 0 \end{matrix}

[1] Correspondence author: Henrique Gazzetta Junior | Avenida Cassiano Ricardo, 1.411 - Apto. 84B | CEP: 12.240-540 - São José dos Campos/SP - Brazil | E-mail: henrique.gazzetta@gmail.com

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Run time Assessment for Gas Turbine Performance Simulation

ABSTRACT: