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**Harvard**

Sammak, M., Genrup, M., Thorbergsson, E., Grönstedt, T., Jonshagen, K., Thern, M. och Dahlquist, A. (2011) *Conceptual Design Of A Mid-Sized Semi-Closed Oxy-Fuel Combustion Combined Cycle*.

** BibTeX **

@conference{

Sammak2011,

author={Sammak, Majed and Genrup, Magnus and Thorbergsson, Egill and Grönstedt, Tomas and Jonshagen, Klas and Thern, Marcus and Dahlquist, Adrian},

title={Conceptual Design Of A Mid-Sized Semi-Closed Oxy-Fuel Combustion Combined Cycle},

booktitle={Proceedings of the ASME Turbo Expo 2011: Power for Land, Sea and Air, 2011, Vancouver, Canada},

isbn={978-079185464-8},

pages={253-261},

abstract={This paper presents the study of a mid-sized semi-closed oxy-fuel combustion combined cycle (SCOC-CC) with net power output around 108 MW. The paper describes not only the power balance and the performance of the SCOC-CC, but also the conceptual design of the SCOC turbine and compressor. A model has been built in the commercial heat and mass balance code IPSEpro to estimate the efficiency of semi-closed dual-pressure oxy-fuel combustion combined cycle using natural gas as a fuel. In order to obtain the real physical properties of the working fluids in IPSEpro, the code was linked to the NIST Reference Fluid Thermodynamic and Transport Properties Database (REFPROP).
The oxy-fuel turbine was modeled with the in-house Lund University package LUAX-T. Important features such as stage loading, loss modeling, cooling and geometric features were included to generate more accurate results. The oxy-fuel compressor has been modeled using a Chalmers university in-house tool for conceptual design of axial compressors. The conceptual design of the SCOC-CC process has a net efficiency of 47 %. The air separation unit and CO2 compression reduce the cycle efficiency by 10 and 2 percentage points, respectively.
A single-shaft configuration was selected for the gas turbine simplicity. The rotational speed chosen was 5200 rpm and the turbine was designed with four stages. All stage preliminary design parameters are within ranges of established industrial axial turbine design limits. The main issue is the turbine exit Mach number; the stage must be lightly loaded in terms of pressure ratio to maintain the exit Mach number below 0.6. The compressor is designed with 18 stages. The current value of the product of the annulus area and the blade rotational speed squared (AN2) was calculated and found to be 40*10^6.},

year={2011},

keywords={SCOC-CC, Oxy fuel, gas turbine, mid-sized dual pressure combined cycle, CO2.},

}

** RefWorks **

RT Conference Proceedings

SR Electronic

ID 153069

A1 Sammak, Majed

A1 Genrup, Magnus

A1 Thorbergsson, Egill

A1 Grönstedt, Tomas

A1 Jonshagen, Klas

A1 Thern, Marcus

A1 Dahlquist, Adrian

T1 Conceptual Design Of A Mid-Sized Semi-Closed Oxy-Fuel Combustion Combined Cycle

YR 2011

T2 Proceedings of the ASME Turbo Expo 2011: Power for Land, Sea and Air, 2011, Vancouver, Canada

SN 978-079185464-8

SP 253

OP 261

AB This paper presents the study of a mid-sized semi-closed oxy-fuel combustion combined cycle (SCOC-CC) with net power output around 108 MW. The paper describes not only the power balance and the performance of the SCOC-CC, but also the conceptual design of the SCOC turbine and compressor. A model has been built in the commercial heat and mass balance code IPSEpro to estimate the efficiency of semi-closed dual-pressure oxy-fuel combustion combined cycle using natural gas as a fuel. In order to obtain the real physical properties of the working fluids in IPSEpro, the code was linked to the NIST Reference Fluid Thermodynamic and Transport Properties Database (REFPROP).
The oxy-fuel turbine was modeled with the in-house Lund University package LUAX-T. Important features such as stage loading, loss modeling, cooling and geometric features were included to generate more accurate results. The oxy-fuel compressor has been modeled using a Chalmers university in-house tool for conceptual design of axial compressors. The conceptual design of the SCOC-CC process has a net efficiency of 47 %. The air separation unit and CO2 compression reduce the cycle efficiency by 10 and 2 percentage points, respectively.
A single-shaft configuration was selected for the gas turbine simplicity. The rotational speed chosen was 5200 rpm and the turbine was designed with four stages. All stage preliminary design parameters are within ranges of established industrial axial turbine design limits. The main issue is the turbine exit Mach number; the stage must be lightly loaded in terms of pressure ratio to maintain the exit Mach number below 0.6. The compressor is designed with 18 stages. The current value of the product of the annulus area and the blade rotational speed squared (AN2) was calculated and found to be 40*10^6.

LA eng

DO 10.1115/GT2011-46299

LK http://dx.doi.org/10.1115/GT2011-46299

OL 30