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The flow at the entrance to an axial-flow compressor rotor has zero preswirl and an axial velocity of \(175 \mathrm{~m} / \mathrm{s}\). The shaft angular speed is \(5000 \mathrm{rpm}\). If at a radius of \(0.5 \mathrm{~m}\), the rotor exit flow has zero relative swirl, calculate at this radius (a) rotor specific work \(w_{c}\) in \(\mathrm{kJ} / \mathrm{kg}\) (b) degree of reaction \({ }^{\circ} R\)

Short Answer

Expert verified
The rotor specific work \(\displaystyle{w_{c}}\) is \(261.80 \, \mathrm{kJ/kg}\) and the degree of reaction ${ }^{\circ} R = 0$.

Step by step solution

01

Calculate Angular Speed

First, we need to convert the given shaft angular speed from rpm to radian per second. The conversion formula is \( \omega = \frac{2 \pi n}{60} \) where \(n\) is the speed in rpm. Substituting the given \(n = 5000 \, \mathrm{rpm}\) into the equation gives \( \omega = \frac{2 \pi * 5000}{60} \).
02

Calculate Rotor Specific Work

Rotor specific work \(w_{c}\) is calculated as \(w_{c} = \frac{1}{2} \omega^2 r^2\) where \(\omega\) is the angular speed in rad/s and \(r\) is the radius in m. Substituting the calculated \(\omega\) and given \(r = 0.5 \, \mathrm{m}\) into the equation gives \(w_{c} = \frac{1}{2} * \omega^2 * (0.5)^2\). As the result should be in \(\mathrm{kJ/kg}\), convert the result from \(\mathrm{J/kg}\) to \(\mathrm{kJ/kg}\) by dividing by \(1000\).
03

Calculate Rotor Exit Absolute Swirl Velocity

Given the rotor exit flow has zero relative swirl, the absolute swirl velocity \( V_{\theta 2} = 0\).
04

Calculate Degree of Reaction

The degree of reaction \({ }^{\circ} R\) is calculated as \(\frac{1 - (V_{a2}/V_{a1})}{2}\) where \(V_{a2}\) and \(V_{a1}\) are the axial velocities at the exit and entrance. However, since the axial velocities at both the entrance and the exit are the same (\(V_{a2} = V_{a1} = 175 \, \mathrm{m/s}\)), the formula simplifies to \({ }^{\circ} R = \frac{1 - 1}{2}\).

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Key Concepts

These are the key concepts you need to understand to accurately answer the question.

Angular Speed Conversion
Understanding angular speed conversion is essential when working with rotating machinery, such as axial-flow compressors. Angular speed, often measured in revolutions per minute (rpm), needs to be converted to radians per second (rad/s) for use in formulas applicable to physics and engineering.

The conversion formula is quite simple: \[\omega = \frac{2 \pi n}{60}\], where \(\omega\) is the angular speed in rad/s and \(n\) is the speed in rpm. In our case, converting the given shaft speed of 5000 rpm using the formula yields an angular speed in rad/s, which is the standard unit in equations describing rotational motion.
Rotor Specific Work Calculation
The rotor specific work is the amount of work imparted to a fluid per unit mass by the rotor of a compressor. For an axial-flow compressor, this can be expressed mathematically as \[w_{c} = \frac{1}{2} \omega^2 r^2\]. Here, \(\omega\) represents the angular speed in rad/s and \(r\) is the rotor radius in meters.

After performing the angular speed conversion, one can substitute the values to find the specific work. It is crucial to note the resulting specific work will initially be in Joules per kilogram (J/kg). To express the answer in the more common unit of kilojoules per kilogram (kJ/kg), one simply divides the result by 1000. The process highlights the significance of unit conversion for consistency and clarity in engineering calculations.
Degree of Reaction
The degree of reaction in the context of a compressor rotor is defined as the fraction of the total enthalpy change of the fluid which occurs due to changes in static pressure. In technical terms for an axial-flow compressor, it can be represented as \[{}^\circ R = \frac{1 - (V_{a2}/V_{a1})}{2}\], where \(V_{a1}\) is the axial velocity at rotor entrance and \(V_{a2}\) the axial velocity at rotor exit.

In scenarios where the axial velocity remains constant through the rotor—like in the given exercise—the degree of reaction will be zero. This result implies that there is no change in static pressure; all the energy transfer in the rotor is due to changes in the fluid's kinetic energy.
Axial Velocity
Axial velocity is a critical component in determining the behavior and characteristics of fluid flow through a compressor. It represents the speed at which the fluid moves along the axial (or lengthwise) direction of the machine. In compressors, a consistent axial velocity (\[V_{a}\]) indicates a stable flow through the device.

The principle that axial velocity at the entrance (\[V_{a1}\]) and exit (\[V_{a2}\]) of the compressor should ideally be equal is often part of the design criteria, ensuring smooth operation and effective compression. Therefore, a change or difference in axial velocities can significantly affect the degree of reaction, as well as the overall performance of the compressor.

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Most popular questions from this chapter

Apply Euler turbine equation to a streamtube that enters a compressor rotor blade row at \(r=2.5 \mathrm{ft}\) with zero preswirl and exits the row at \(r=2.7 \mathrm{ft}\) and attains \(1000 \mathrm{ft} / \mathrm{s}\) of swirl velocity in the absolute frame. Assume that the shaft rotational speed is \(5000 \mathrm{rpm}\).

The pitchline radius of a compressor rotor is at \(r_{\mathrm{m}}=\) \(0.3 \mathrm{~m}\). The degree of reaction is \({ }^{\circ} R_{\mathrm{m}}=0.75\). The axial velocity to the rotor is \(C_{21}=175 \mathrm{~m} / \mathrm{s}=\) constant across the blade row. The flow to the rotor has zero preswirl and the rotor angular speed is \(\omega=6500 \mathrm{rpm}\). The solidity of the rotor at the pitchline is \(\sigma_{\mathrm{m}}=1.0\). Calculate: (a) absolute swirl velocity downstream of the rotor, i.e., \(\mathrm{C}_{82 \mathrm{~m}}\), in \(\mathrm{m} / \mathrm{s}\) (b) relative swirl upstream and downstream of the rotor, i.e., \(W_{\theta 1}\) and \(W_{\theta 2}\) in \(\mathrm{m} / \mathrm{s}\) (c) de Haller parameter, \(W_{2} / W_{1}\) (d) diffusion factor at the pitchline radius, \(D_{\mathrm{m}}\)

A multistage compressor develops a total pressure ratio \(\pi_{c}=25\), and is designed with eight identical (i.e., "repeated") stages. The compressor polytropic efficiency is \(e_{\mathrm{c}}=0.92\). Calculate (a) average stage total pressure ratio \(\pi_{\mathrm{s}}\) (b) stage adiabatic efficiency \(\eta_{\mathrm{s}}\) (c) compressor total temperature ratio \(\tau_{c}\)

An axial-flow compressor stage at its pitchline radius \(\left(r_{\mathrm{m}}=0.50 \mathrm{~m}\right)\) has zero preswirl, an axial velocity of \(150 \mathrm{~m} / \mathrm{s}\). Its degree of reaction is \({ }^{\circ} R_{\mathrm{m}}=0.50\), and the shaft angular speed is \(5,200 \mathrm{rpm}\). Assuming constant throughflow speed, i.e., \(C_{\mathrm{z}}=\) const., and repeated stage design at the pitchline, calculate: (a) relative Mach number at rotor inlet, \(M_{1 \mathrm{r}}\) (b) rotor exit relative velocity, \(W_{2}(\mathrm{~m} / \mathrm{s})\) (c) static temperature downstream of the rotor, \(T_{2}(\mathrm{~K})\) (d) absolute Mach number downstream of the rotor, \(M_{2}\) (e) absolute Mach number downstream of the stator, \(M_{3}\) (f) stage total temperature ratio, \(\tau_{\mathrm{s}}\) (g) stage total pressure ratio if \(\eta_{s}=0.90\)

An axial-flow compressor rotor at the pitchline has a radius of \(r_{\mathrm{m}}=0.35 \mathrm{~m}\). The shaft rotational speed is \(\omega=\) \(5000 \mathrm{rpm}\). The inlet flow to the rotor has zero preswirl and the axial velocity is \(C_{z 1}=C_{z 2}=C_{z 3}=175 \mathrm{~m} / \mathrm{s}\). The rotor has a \(50 \%\) degree of reaction at the pitchline. The stage adiabatic efficiency is nearly equal to the polytropic efficiency \(\eta_{\mathrm{s}} \cong e_{\mathrm{c}}=\) \(0.92\). Assuming the inlet total temperature is \(T_{\mathrm{t} 1}=288 \mathrm{~K}\) and \(c_{p}=1.004 \mathrm{~kJ} / \mathrm{kg} \cdot \mathrm{K}\), calculate (a) rotor specific work at \(r=r_{\mathrm{m}}\) (b) stage loading \(\psi\) at \(r=r_{\mathrm{m}}\) (c) flow coefficient at \(r=r_{\mathrm{m}}\) (d) rotor relative Mach number at the pitchline, \(M_{1 r, m}\) (e) stage total pressure ratio at the pitchline

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