Last Updated On [03-11-2023]
.png)
The given diagram represents the velocity triangles at the leading edge (1) and trailing edge (2) at the mean radius of a single stage axial compressor rotor. The stage efficiency of the compressor is 0.8. The stagnation temperature of air entering the stage is $298 \mathrm{~K}$ and the specific heat at constant pressure for air is $1.005 \mathrm{~kJ} / \mathrm{kgK}$. The ratio of specific heats for air is 1.4. Considering actual work in the rotor is equal to the ideal work, the pressure ratio for the stage is equal to ___________(in two decimal points).
Question ID - 155595 :-
The given diagram represents the velocity triangles at the leading edge (1) and trailing edge (2) at the mean radius of a single stage axial compressor rotor. The stage efficiency of the compressor is 0.8. The stagnation temperature of air entering the stage is $298 \mathrm{~K}$ and the specific heat at constant pressure for air is $1.005 \mathrm{~kJ} / \mathrm{kgK}$. The ratio of specific heats for air is 1.4. Considering actual work in the rotor is equal to the ideal work, the pressure ratio for the stage is equal to ___________(in two decimal points).
The given diagram represents the velocity triangles at the leading edge (1) and trailing edge (2) at the mean radius of a single stage axial compressor rotor. The stage efficiency of the compressor is 0.8. The stagnation temperature of air entering the stage is $298 \mathrm{~K}$ and the specific heat at constant pressure for air is $1.005 \mathrm{~kJ} / \mathrm{kgK}$. The ratio of specific heats for air is 1.4. Considering actual work in the rotor is equal to the ideal work, the pressure ratio for the stage is equal to ___________(in two decimal points).
Next Question :
An aircraft with a turbojet engine, having an inlet area of $1 \mathrm{~m}^{2}$, is flying at $270 \mathrm{~m} / \mathrm{s}$ at an altitude where the atmospheric pressure is equal to 0.9 bar and the ambient temperature is equal to $290 \mathrm{~K}$. The stagnation pressure and temperature at the exit of the turbine are equal to 1.6 bar and $774 \mathrm{~K}$ respectively. The specific heat at constant pressure of the burned gases is equal to $1.147 \mathrm{~kJ} / \mathrm{kgK}$ and the ratio of specific heats is equal to 1.33. Considering ideal expansion in the nozzle with no losses, the specific thrust produced by the engine is______________ $\mathrm{Ns} / \mathrm{kg}$ (in one decimal place).
View Topper Answer
We hope we have given the updated helpful answer / content for your query in an easily accessible format to help you in preparing adequately. We do offer free support materials, 11th maths guide 11th maths guide 12th maths guide 10th maths guide, also for all the classes books and guide to all the students who sign up for SaraNextGen. Apart from traditional textbook queries, we've got conjointly provided further high order level thinking issues, that are seemingly to be expected in boards and competitive exams. It includes conceptual queries, MCQs, Long and short answer type queries, etc. These Questions are designed to learn each student and academics by providing chapter-wise further issues focusing totally on testing conceptual information with applications. Here, we've got provided a number of the necessary ways in which within which the solutions of all the Questions will profit students of class 1 to 12. If you have any queries, drop a message to us and we will get back to you at the earliest.
