JNTU
JNTU B.Tech IV Year TURBO MACHINERY Previous Question Paper (July/August - 2022 - R18)
Answer any five questions. All questions carry equal marks.
Main
What is preheat factor in a multistage compressor? Prove that preheat factor is less than unity.
Answer
The preheat factor in a multistage compressor is defined as the ratio of the sum of the isentropic enthalpy rises of individual stages to the isentropic enthalpy rise of the overall compression process from the initial pressure to the final pressure. It accounts for the fact that the increase in enthalpy due to stage inefficiency (irreversibility) in one stage increases the inlet temperature of the subsequent stage, thereby increasing the work required for the same pressure ratio.
Mathematically, if Δh_s is the isentropic enthalpy rise of a single stage and ΔH_s is the isentropic enthalpy rise of the total process, the preheat factor (F) is given by:
To prove F > 1 (note: the preheat factor is typically greater than unity for compressors, while the reheat factor is less than unity for turbines):
- In a compressor, the constant entropy lines on an h-s diagram diverge as pressure increases.
- The isentropic enthalpy change for a given pressure ratio increases as the initial temperature increases.
- Because stage inefficiencies cause the actual temperature at the exit of a stage to be higher than the isentropic exit temperature, the subsequent stages operate at higher temperature levels.
- Consequently, the sum of the individual isentropic enthalpy rises (ΣΔh_s) is greater than the isentropic enthalpy rise of the overall process (ΔH_s) between the same total pressure limits, resulting in a preheat factor greater than unity.
What is infinitesimal stage efficiency in the expansion through a turbine? How is it determined?
Answer
Infinitesimal stage efficiency, also known as polytropic efficiency, is the efficiency of an infinitesimally small stage in a turbine where the change in pressure and temperature is negligible. It represents the efficiency of the expansion process at any point along the expansion line, independent of the total pressure ratio.
It is determined by considering the ratio of the actual work done to the isentropic work done for an infinitesimal pressure change:
For an ideal gas undergoing an expansion process, this is expressed in terms of temperature and pressure changes:
By integrating this relationship between the initial and final states, the polytropic efficiency can be related to the overall isentropic efficiency of the turbine. It is a useful design parameter because it remains nearly constant throughout the expansion process, allowing designers to predict the performance of turbines across varying pressure ratios without the influence of the reheat effect.
Define a turbo machine. What are the main differences between incompressible and compressible flow machines?
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An air compressor has eight stages of equal pressure ratio 1.3. The flow rate through the compressor and its overall efficiency are 45 kg/s and 80% respectively. If the conditions of air at entry are 1 bar and 350C, determine (i) state of air at compressor exit, (ii) polytropic efficiency (iii) efficiency of each stage.
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Give three formulas to calculate the slip factor. Derive Stodola’s relation for the slip factor.
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A single stage centrifugal pump with impeller diameter of 30 cm rotates at 2000 rpm and lifts 3 m3 of water per second to a height of 30 m with an efficiency of 75%. Find (i) the number of stages and (ii) the diameter of each impeller of a similar multistage pump to lift 5 m3 of water per second to a height of 200 m, when rotating at 1500 rpm.
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Obtain the Euler’s Energy transfer equation for rotating bodies. Explain.
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What is slip factor? What is its effect on the flow and the pressure ratio in the stage? Discuss.
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Write the four basic equations that satisfy the state points before and after a normal shock and hence deduce that at the maximum entropy point on the h-s diagram the mach number is unity.
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A centrifugal compressor runs at a speed of 550 m/s with no prewhirl. Suppose the slip is 0.95 and isentropic efficiency of compressor is 0.85. Calculate the following for standard sea level: (i) Pressure ratio, (ii) the work required, and (iii) the power required. Assume mass flow rate of 25 kg/sec and Cp = 1.005 kJ/kg K and ambient temperature of 150C.
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An inward flow radial turbine has the following data: Power 150 kW, Speed 32000 rpm, Outer diameter of the impeller 20 cm, Inner diameter of the impeller 8 cm, Absolute velocity of gas at entry 387 m/s, Absolute velocity of gas at exit 193 m/s (radial). The gas enters the impeller radially. Construct the velocity triangles at the entry and exit of the impeller and determine: (a) the mass flow rate and (b) the percentage energy transfer due to the change of radius.
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What is the work done factor for an axial compressor stage? Why it is not employed for turbine stages?
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Draw a sketch of an axial flow compressor cascade. Show the stagger angle, incidence (positive and negative) and deviation angles. Prove that ε = θ + i - δ.
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Explain the following:
(a) Correlations of Soderberg and Hawthorne in turbine cascade analysis.
(b) Secondary flow in the axial turbine and compressor cascades.
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