$2\mathrm{.}1.$ A single$-$stage axial flow turbine operates with an inlet temperature of $1100$ K and a total pressure of $3\mathrm{.}4$ bar. The total temperature drop across the stage is $144$ K $,$ and the isentropic efficiency is $0\mathrm{.}9.$ The mean blade speed is $298\frac{m}{s},$ and the mass flow rate is $18\mathrm{.}75k\frac{g}{sec}.$ The turbine operates with a rotational speed of $12000$ rpm if the convergent nozzle operates under choked conditions.

$2\mathrm{.}1\mathrm{.}1$ draw clear combined velocity triangles

$(4)$

$2\mathrm{.}1\mathrm{.}2$ blade$-$loading coefficient

$(3)$

$2\mathrm{.}1\mathrm{.}3$ pressure ratio of the stage.

$2\mathrm{.}1\mathrm{.}4$ the temperature ratio

$2\mathrm{.}1\mathrm{.}5$ the axial velocity

$(2)$

$2\mathrm{.}1\mathrm{.}6$ the flow angle at the inlet of the rotor

$(2)$

$2\mathrm{.}1\mathrm{.}7$ the blade angle at the inlet of the rotor

$2\mathrm{.}1\mathrm{.}8$ the flow angle at the exit of the rotor

$2\mathrm{.}1\mathrm{.}9$ the blade angle at the exit of the rotor

$(2)$

$[25]$