Gas Turbine Problems

Gas Turbine Problems Summer 2013

1. A gas turbine turbine unit has a pressure pressure ratio ratio of 6 and maximum maximum ccle temperatur temperature e of 610!". The isentropic e#cienc of the turbine and compressor are 0.$2 and 0.$ respecti%el. "alculate the po&er output in '( &hen the air enters the compressor at 1)!" at a rate of 16 *g+s. Ta*e "p, 1.00) '-+*g ' and  , 1./ for compression process and "p, 1.11 '-+*g ' and  , 1.333 for expansion process. (inter 2012

2. "alculate the the e#cienc and specic specic &or* output output of a simple simple gas turbine turbine plant operating on raton ccle. The maximum and minimum temperatures are 1000' and 2$$' respecti%el. The pressure ratio is 6.The isentropic e#cienc of  the compressor and turbines are $) and 0 respecti%el. 4f the unit consumes 2 tonnes of oil per hour of caloric %alue /6)00 '- per *g5 determine the po&er generated .The mechanical e#cienc is 0) and generation e#cienc is $).  a+-une 2012

3. 4n an open gas turbine turbine plant5 the pressur pressure e ratio through through &hich air at at 1) !" is compressed is 1/. The same air is then heated to a maximum permissible temperature of 1300 !" rst in a heat exchanger &hich is 7) e#cient5 and then in the combustion chamber. The air at 1300 !" is expanded in t&o stages such that the expansion &or* is the maximum. The air is heated to 1300!" after the high pressure stage. 8etermine the ccle thermal e#cienc5 the &or* ratio and the net shaft &or* per *g of air. The isentropic e#ciencies ma be assumed to be $) and $6 for compressor and turbine respecti%el. "alculate the 9o& rate of air for an output of 2/0 (. Assume echanical and Generator e#cienc 0. (inter 2011

/. A gas turbine turbine po&er plant plant operates operates bet&een bet&een temperatures temperatures 1) !" and 1100!" 1100!" . "alculate the follo&ing: ;i< The optimum pressure ratio for the ccle for maximum po&er output5 ;ii< "ompressor &or*5 Turbine &or*5 Shaft &or* and (or* =atio5 and ;iii< Plant e#cienc. Ta*e for air5 "p,1.00) *-+*g>' and * , "p + "% , 1./. (inter 2010

). The air enters the the compressor compressor of an open open ccle constant constant pressure pressure gas turbine turbine at a pressure of 1 bar and temperature of 20!". The pressure of the air after compression is / bar. The isentropic e#cienc of compressor and turbine are $0  and $)  respecti%el. The air fuel ratio used is 0: 1. 4f the 9o& rate of air is 3 *g per second ?ind5 ;i< Po&er de%eloped

;ii< Thermal e#cienc of the ccle Assume5 "p , 1 *-+*g' and  , 1./5 for air @gas and "..of fuel , /1$00*-+*g