A single-stage gas turbine operates with an axial absolute flow at the entry and exit from the stage. The absolute flow angle at the nozzle exit is $70^{\circ}$. The turbine stage generates a specific work of $228 \mathrm{~kJ} / \mathrm{kg}$ when operating with a mean blade speed of $440 \mathrm{~m} / \mathrm{s}$. The absolute velocity at the rotor entry is

(A) $275.7 \mathrm{~m} / \mathrm{s}$

(B) $551.5 \mathrm{~m} / \mathrm{s}$

(C) $1103.0 \mathrm{~m} / \mathrm{s}$

(D) $1654.5 \mathrm{~m} / \mathrm{s}$

A single-stage gas turbine operates with an axial absolute flow at the entry and exit from the stage. The absolute flow angle at the nozzle exit is $70^{\circ}$. The turbine stage generates a specific work of $228 \mathrm{~kJ} / \mathrm{kg}$ when operating with a mean blade speed of $440 \mathrm{~m} / \mathrm{s}$. The absolute velocity at the rotor entry is

(A) $275.7 \mathrm{~m} / \mathrm{s}$

(B) $551.5 \mathrm{~m} / \mathrm{s}$

(C) $1103.0 \mathrm{~m} / \mathrm{s}$

(D) $1654.5 \mathrm{~m} / \mathrm{s}$

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