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**ME 423 Chapter 5 Axial Flow Compressors**

Prof. Dr. O. Cahit ERALP

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**Chapter 5 Axial Flow Compressors**

Subsonic compressors will be considered here as supersonic compressors have not proceeded beyond experimental stage. A Comparison of Axial Flow Compressors and Turbines Turbine :- Accelerating flow - Successive pressure drops and consequent reductions in enthalpy being converted into kinetic energy A1>A2 ⇨ converging passages Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**A Comparison of Axial Flow Compressors and Turbines**

Compressor :- Decelerating flow - Pressure rises are obtained through successive stages of diffusing passages with consequent reduction in velocity. A1<A2 ⇨ diverging passages Problems of compressors & turbines are different in compressors - aerodynamic problems in turbines - problems due to entry temperature and heat-transfer. Boundary Layers - regions of low momentum air where viscous effects dominate over inertial effects. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**A Comparison of Axial Flow Compressors and Turbines**

Boundary layers are far less happy in a compressive flow. BL in a compressor operate in an unfavourable pressure gradient [(+) 've ; p increase ] BL in a turbine operate in a favourable pressure gradient [ (-)'ve ; p decrease. ] This is the reason why a single stage turbine can create enough power to drive a number of stages of compressor. Bend thin plates and stick them behind each other forming a stationary cascade of blades. Let the flow be directed towards the inlet of this cascade of blades without any incidence. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**A Comparison of Axial Flow Compressors and Turbines**

As A2 > A1 in subsonic flow (incompressible) W2 < W1 & P2 > P1 This is no more than a subsonic diffuser To carry a mechanical load, some thickness is required. If M < incompressible i.e thus Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**A Comparison of Axial Flow Compressors and Turbines**

Clearly the outlet velocity W2 cannot decrease beyond a certain level (cannot be zero) (or W2 ≠ 0) p W12 (since W2 is fixed by the lower limit) One should design the compressor at the highest inlet velocity But the losses ⇨ Po α W12 α 1/ p Stage pressure ratio is limited and the number of stages are determined accordingly (single stage or multistage) Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**A Comparison of Axial Flow Compressors and Turbines**

Due to the contraction, the flow initially accelerates pressure drops (favourable to BL) ( A1 > A1' ) then The amount of pressure rise between 1' to 2 is larger than that of 1 to 2. i.e more diffusion the limit of Wmax is than of sonic limit. More diffusion means less efficiency i.e why we prefer compressor blades to be as thin as possible. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**A Comparison of Axial Flow Compressors and Turbines**

The more the (camber), the more is the adverse pressure gradient, then seperation occurs earlier. The seperated flow leaves the blade at an unwanted angle and unsteady situation. All these problems in compressor cascades are due to Boundary layers. Turbine problems are completely different since we want the pressure to drop along the flow direction. The flow is a high "h" enthalpy or high temperature, high pressure (to low T low P) flow. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**A Comparison of Axial Flow Compressors and Turbines**

The blades are such that minimum c/s area occurs at the trailing edge of the blades which is called the throat. The flow area should contract continuously all the way along the blades in order not to have an adverse pressure gradient BL along the row. Even an instantaneous discontinuity in the contraction of the passage results in a locally seperated BL, thus increased turbulence. This might happen due to simplified manufacture for curvatures such as two circles. This results in extremely high heat transfer coefficient, thus the blade will not last 10 minutes. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**A Comparison of Axial Flow Compressors and Turbines**

For the Axial Compressors and turbines the basic components are rotors and stators, the former carrying the rotating blades and the latter the stationary rows which serve to recover the pressure rise from the kinetic energy imparted to the fluid by the rotor blades as in compressors and/or to redirect the flow into an angle suitable for entry to the next row of moving blades. A compressor stage is composed of a rotor followed by a stator, where as a turbine stage is composed of a stator followed by a rotor . Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**A Comparison of Axial Flow Compressors and Turbines**

In Compressors It is usual to provide a row of stator blades –Inlet Guide Vanes (IGV's) at the upstream of the first stage. These direct the axially approaching flow correctly into the first row of rotor blades. Thus deflect the flow from axial direction to off-axial direction. IGV's are turbine type of blades. Two forms of rotor construction is used Drum type-suitable for industrial applications Disc type - suitable for aircraft applications low weight, high cost) Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**A Comparison of Axial Flow Compressors and Turbines**

Another important constructional detail is the contraction of the flow annulus from the low the high pressure end of the compressor. This is necessary to maintain a reasonably constant axial velocity along. most compressors are designed on the basis of constant axial velocity because of the simplification in design procedure. One could have a rising hub or a falling shroud in compressors. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Elementary Theory For Axial Flow Compressors**

Basic principle : Acceleration of the working fluid followed by diffusion to convert the acquired kinetic energy into a pressure rise. The flow is considered as occuring in the tangential plane at the mean blade height where the blade peripheral velocity is u. When the annulus is unrolled, since the blade C/S changes from Hub to Tip, one C/S is chosen (e.g. at mid blade height) and a series of constant C/S aerofoils result. These are called a 2-D cascade of aerofoils. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Elementary Theory For Axial Flow Compressors**

A semi- cascade can be produced if the cascade end boundary effects are eliminated (The flow in the channels are not aware of what happens at the ends) The aerodynamics of a cascade repeats itself with a periodicity of s (pitch). As the flow is going through the cascade, the end wall BL grows in thickness, thus the axial velocity grows. To take care of this, BL is sucked; or a large "Aspect Ratio" cascade where the effect of end wall BL is less observed, is used. v-absolute velocity w-relative velocity u- peripheral blade velocity Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Elementary Theory For Axial Flow Compressors**

On the rotor, turn your head into the wind, and the drought you feel is the relative velocity w Connect the absolute velocity vectors (u and v) together arrow-head to arrow-head, the tails became the relative velocity vector (w) W2< W P2 > P1 across the rotor across the stator Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Elementary Theory For Axial Flow Compressors**

From the velocity triangles U/Va= tan 1 + tan 1 (5.1) U/Va= tan 2 + tan 2 (5.2) The axial velocity Va is assumed to be constant throughout the stage. The work absorbed by the stage, from the consideration of the"change of angular momentum", in terms of work done per unit mass flow rate or specific work input is: (5.3 , 5.4) or (5.5) Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Elementary Theory For Axial Flow Compressors**

Vθ2 – Vθ1 Vθ2 Vθ1 U Va exit W2 V1 inlet β1 α1 V2 α2 β2 Combined Velocity Triangle for Axial Compressor Stage Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Elementary Theory For Axial Flow Compressors**

The input energy is absorbed usefully to increase p and v and waste fully to increase T (frictional losses) regardless of losses (efficiency) the whole input = Tos If V1 = V3 (5.6) In actual fact the stage temperature rise will be less than this owing to 3D effects in the compressor annulus (growing end wall B/L) Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Elementary Theory For Axial Flow Compressors**

Analysis of experimental results has shown that it is necessary to multiply the results given by equation 5.6 by the so called work done factor which is a number < 1 λ = Actual work absorbing capacity / Ideal work absorbing capacity The explanation of this is based on the fact that the radial distribution of axial velocity is not constant across the annulus but becomes increasingly peaky as the flow proceeds as shown in the figure. From eqn. 5.1 : Va tan 1 = U- Vatan 1 Substitute into 5.5 : since 1 & 1 are fixed while Va increase then w decrease Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Elementary Theory For Axial Flow Compressors**

Va Va mean From eqn. 5.1 : Va tan 1 = U- Vatan 1 Substitute into 5.5 : since 1 & 1 are fixed while Va increase then w decrease Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Elementary Theory For Axial Flow Compressors**

If the compressor has been designed for a constant radial distribution of Va, the effect of an increase in Va in the central region will be to reduce the work capacity of blading in that area. This reduction however should be compensated by increases in the regions of the root and tip of the blading because of the reductions in Va at these parts of the annulus. Unfortunately this is not the case since; Influence of BL's on the annulus walls Blade tip clearances has an adverse effect on this compensation and the net result is a loss in total work capacity) .W = Actual amount of work which can be supplied to the stage. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Elementary Theory For Axial Flow Compressors**

Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Elementary Theory For Axial Flow Compressors**

Actual stage temperature rise : The pressure ratio: s= stage isentropic efficiency Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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** = static pressure rise across the rotor / **

Degree of Reaction = static pressure rise across the rotor / / static pressure rise across the whole stage It is also a measure of how much of the total pressure rise across the stage occurs in the rotor. Since Cp doesn't vary much across a stage, will be equal to the corresponding temperature rises. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**TR = Temperature rise across the rotor **

Degree of Reaction TR = Temperature rise across the rotor TST = Temperature rise across the stator TS = Stage temp. Rise Assuming =1.0 Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**The steady flow energy eqn : with eqn (5.8) : But**

Degree of Reaction The steady flow energy eqn : with eqn (5.8) : But since Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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Degree of Reaction (5.9) Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**For 50% reaction which is a wide practice (=0.50)**

Degree of Reaction For 50% reaction which is a wide practice (=0.50) from equations 5.1 & 5.2 ⇨ 1 = 2 , 2 = 1 since V1=V3 1 = 3 (for repeating stages) For ⇨ symmetrical blading 1 = 2 = 3 , 1 = 2 Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**but still will be called symmetrical blading.**

Degree of Reaction Eqn 5.9 is derived for =1 Actually will differ from 50% slightly because of the influence of ; but still will be called symmetrical blading. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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3D Flow Up to here the analysis has been confined to a 2D flow basis at one particular radial position in the annulus ; which is usually chosen to be "at the mean blade height" Before considering its extension to cover the whole blade height , attention must be given to some basic principles of 3D flow. For high H/T ratio 2D assumption is reasonable Low H/T ratio Radial flow components should be considered. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Basic Assumption V r =0 at the entry and exit of a blade row. **

3D Flow Assumption Any radial flow within the annulus occurs only while the fluid is passing through the blade rows. The flow in the gaps between successive blade rows will be in Radial Equilibrium. Basic Assumption V r =0 at the entry and exit of a blade row. A commonly used design method is based on this principle and an equation is set up to fulfill the requirement that radial pressure forces must act on the air elements in order to provide the necessary radial acceleration associated with the peripheral velocity component V. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**3D Flow p+dp dr Vθ p+dp/2 p r dθ Me 423 Spring 2006**

Prof. Dr. O. Cahit ERALP

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**(Radial Equilibrium Condition)**

3D Flow From the figure the force balance in radial direction i.e pressure forces = centrifugal forces Vr =0 Here for small Cancelling dq through the eqn and neglecting 2nd orderterms such as dpdr. (Radial Equilibrium Condition) Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Radial Equilibrium Condition**

The Radial equilibrium equation may be used: to determine Va (r) once V(r) is chosen (design or indirect problem) to determine Va (r), V (r) produced by a selected blade shape i.e. a (r) (Direct problem) The stagnation enthalpy "h0" at any radius r since Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Radial Equilibrium Condition**

Differentiating wrt. r we have Lets assume that the change in pressure across the annulus is small and the isentropic relation can be used. i.e =const. is valid with little error. In differential form OR substituting into the previous relation; Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Radial Equilibrium Condition**

Introducing the Radial Equilibrium condition Apart from the regions near the walls of the annulus the stagnation enthalpy (and To) is uniform across the annulus at the entry to the blade rows. Thus in any plane between a pair of blade rows. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Radial Equilibrium Condition**

A special case may now be considered in which Va=const. is maintained across the annulus, so that OR Integrating this gives: OR Thus the whirl velocity component of the flow varies inversely with the radius. This is the Free Vortex condition. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Radial Equilibrium Condition**

The Free Vortex Radial Equilibrium is Satisfied by: Constant specific work input dho/dr = 0 Constant axial velocity at all radii i.e. dVa/dr =0 Free Vortex variation of whirl velocity (Vr =const) Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Radial Equilibrium Condition**

There is no reason why the specific work input should not be varied with radius i.e It would then be necessary to choose a radial variation of one of the other variables say Va (r) and determine the variation of V with r to satisfy the radial equilibrium. Thus in general a design can be based on arbitrarily choosen radial distributions of any two variables and the appropriate variation of the third can be determined by using the equation Note: or any other variable may be used instead of Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP Method of Design Work**

Variations with radius ho(r) Tangential velocity Distibution Vθ(r) Axial velocity distribution with Radius Va(r) Reaction Radius Λ(r) Radial Equilib. Remarks A Two- Dimensional Supposed constant Supposed constant Ignored All variations of flow with radius are ignored Method for: high H/T stages B Free Vortex Constant Vθr = constant Incresed with radius Yes Limited by high rotor root deflection (approx. const. stator defl.) C Constant (without equilibrium) Vθ = ar ± b/r Λ and work distr. will NOT be const. since true variation in Va is not considered D Constant From radial equilib. Logical design method Highly twisted blades E Half Vortex Arithmetic mean of free vortex and const. reaction dist. Not far from const. Λ and work distr. will NOT be const. since true variation in Va is not considered F Constant α2 Fixed by condition Vθ2 = cost. [stator entry] Vθ1 = a – b/r [rotor entry] Widely used but its performance and advantages not widely understood G Forced Vortex Increases with r2 Vθ α r Varies with radius Rarely used H Exponential Vθ = a ± b/r A logicl design method Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Air Angles Blade angles Blade Geometry **

Blade Design Having determined the air angle distributions to give the required stage work it is now necessary to convert these into blade angle distributions from which the correct geometry of the blade forms may be determined. Air Angles Blade angles Blade Geometry The common practice is to use the results of the wind tunnel tests to determine the blade shapes to give the required air angles. The aim of the cascade testing is to determine the required angles for Maximum mean deflection Minimum mean total head loss. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Blade Design β1v,α1v = Blade inlet angle β2v,α2v = Blade outlet angle**

β1, α1 = Air inlet angle β2, α2 = Air outlet angle W1,V1 = Air inlet velocity W2,V2 = Air outlet velocity s = pitch c = chord θ = camber = α1v – α2v ξ = stagger = 0.5(α1v + α2v) є = deflection = α1 – α2 i = incidence = α1 - α1v δ = deviation = α2 – α2v Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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Blade Design Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**The loss in non-dimensional form w = **

Blade Design The loss in non-dimensional form w = It is desirable to avoid numbers with common multiples for the blades in successive rows to reduce the likelihood of introducing resonant frequencies. The common practice is to choose an even number for the stator blades and a prime number for the rotor blades. The blade outlet angle “2v” can not be determined from the air outlet angle “2” until the deviation angle “” has been determined. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Blade Design β2 α2 β1 ε = β1 – β2 β2 ε* s/c s c h h/c rm n**

β2 α2 nr prime ns even β1 ε = β1 – β2 β2 ε* s/c s c h h/c know how ≈ 3 rm n n = 2πrm/s number of blades Des. Defl. Curve recalculate s/c , h/c Design Procedure Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Empirical equations are employed to estimate . where : **

Blade Design Ideally the mean direction of the air leaving the cascade would be that of the outlet angle is of the blades. But in practice it is found that there is a deviation which is due to the reluctance of the air to turn through the full angle required by the shape of the blade. Empirical equations are employed to estimate . where : where "a" = the distance to the point of maximum camber from the leading edge. If the camber arc is circular (2 a/c) = 1 Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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Blade Design Using the values of “c, 1v, 2v, “ ; it is possible to construct the circular arc camber line of the blade around which an aerofoil section can be built up. This method can now be applied to a selected number of points along the blade length to get a complete picture of the blade form. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

After the completion of stage design it will now be necessary to check over the performance, particularly in regard to the efficiency which for a given work input will completely govern the final pressure ratio. This efficiency is dependent of the total pressure drop for each of the blade rows comprising the stage and in order to evaluate these quantities it will be necessary to revert the loss measurements in cascade tests. Lift and profile drag coefficients CL and CDP can be obtained from measured values of mean loss w. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

The static pressure rise across the blades is given by (incompressible assumption) Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

Assuming Va = Va1 = Va2; The axial force per unit length of each blade is = s P From the consideration of momentum changes the forces acting along ethe cascade is given by F = s Va change in tangent velocity component along the cascade F = sVa *Va (tan1 - tan2) Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

The coefficients CL and CDP are based on arbitrarily defined vector mean velocity Vm, where D = Drag force along vector mean velocity L = Lift force perpendicular to vector mean velocity Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

After some manipulations CDP and CL can be evaluated if a Howell like curve is known from cascade test results and Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

CDP CL İncidence i degrees Drag coefficient CDP Lift coefficient CL 0.075 -10 -5 5 10 0.5 1.0 1.5 0.025 0.050 -15 -20 Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

Using the values of from cascade test results for known values of (s/c); CDP and CL can be plotted against incidence. Since the value of Cp tan m in CL equation is negligibly small, it is usual to use a more convenient theoretical value of CL given by In which the effect of profile drag is ignored. Using this formula, curves of CL can be plotted for nominal (or design) conditions to correspond with the curves of deflection. These curves are again plotted against 2 for fixed values of s/c Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

Before applying these coefficients to the blade rows of the compressor stage two additional factors must be taken into account. Annulus Drag: Drag effects due to the walls of the Compressor annulus = CDA CDA = 0.02 (s/h) Secondry Losses: Due to the trailing vortices and tip clearances = CDS The following emprical relations can be used CDS = CL2 Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

The overall Drag Coefficient is given by Profile + annulus + secondary (the annular cascade CDP is replaced by CD) thus This enables the loss coefficient for the blade row to be determined. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

The theoretical pressure rise (i.e w =0) Efficiency of the blade row Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

For a case where = 50 % Rotor and stator rows are similar thus this calculation carried at design diameter can be applied to the whole stage for = 1/2 stage efficiency Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

then expanding and neglecting 2nd order terms; for Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Calculation of Stage Performance**

For cases other than 50 % reaction at the design diameter an approximate stage efficiency is given by If far removed from 50% Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Summary of the Design Procedure**

Assume Ts and at the design radius Calculate the air angles Applying chosen design condition (Free Vortex, Constant Reaction etc) Calculate air angles at all radii Results of Cascade Tests Blade shapes (Blade angles) CD and CL Calculate ηs and Rs Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**(η constant through all compressor stages), **

Overall Performance Assuming that ηs = η∞ (η constant through all compressor stages), for a compressor consisting of N similar stages, each with ηs = η∞ R is the “Overall Pressure Ratio” where ; Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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Overall Performance Although the use of polytropic law gives a rapid means of estimating the overall performance of a multistage compressor, it is necessary in practice to make a step by step final performance calculation. Latest blade manufacturing technology allows different blade shapes for different rows. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Compressibility Effects**

High air velocities between the blades effects the compressor performance. Critical Mach number Mc is defined such that at entry velocities lower than this; the performance of the cascade differs very little from that at low speeds. Above this losses begin to show a marked increase. Maximum Mach Number is defined as the air speed at which losses cancel the pressure rise. For a typical low speed cascade Mc = Mm =0.85 Increased Mach number also narrows the operating range of incidence leading to poor performance at off design conditions. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Compressibility Effects**

In the sketch the variations in Mach # across the annulus is shown for Free Vortex and constant reaction blading. Free Vortex blading shown large Mach number variations which extreme care should be taken. Since the velocity of sound in air increases with increasing temperature the Mach numbers will decrease through the compressor due to the progressively increasing temperature. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Compressibility Effects**

Not to suffer from compressibility effects in early stages one might use constant reaction design if no other precaution can be taken. Transonic stages where the flow is actually supersonic over a part of the blade height can now be designed utilizing very thin and special shaped blades. One advantage is eliminating IGV’s less noise. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Some Deductions from the Compressor Characteristics**

The overall compressor characteristic is composed of the stage characteristics stacked. The mass flow through the compressor is controlled by the choking of various stages in some cases early stages, in the others the rear stages. If the axial flow compressor is designed for constant axial velocity throughout ; the annulus area must decrease along due to the increasing density. The annulus area for each stage is determined for the design condition. At any other operating conditon the design point calculated area will result in a variation of axial velocity. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Some Deductions from the Compressor Characteristics**

When the compressor is run at a speed lower than design, T and Rc are reduced than the density at the rear stages will be lower than the design value. As a result the axial velocity at the rear stages will increase, eventually choking will occur. Thus at low speeds m is determined by the choking of the rear stages. As the speed is increased density of the rear stages increases (V decrease) thus gets unchoked. At very high speeds choking will occur at the inlet. The vertical line of constant speed is due to choking at the inlet of the compressor. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Some Deductions from the Compressor Characteristics**

Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Some Deductions from the Compressor Characteristics**

A B At the design speed if we consider the moving of operating point from A to B. At point B (on the surge line), the density at the compressor exit will be increased due to the compressor exit will be increased due to the increase in delivery pressure; also ṁ is slightly reduced. Axial velocity in the last stage is reduced incidence in the last stage is increased. Rotor blades are expected to stall from the last stages. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Some Deductions from the Compressor Characteristics**

Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Some Deductions from the Compressor Characteristics**

ṁ falls rapidly ; Va at the inlet decreases, incidence of the first stage increases. But the incidence of the later stages decrease due to the increase of Va (due to lower pressure and density). At low speeds surging is probably due to first stages stalling. At conditions far removed from surge R is very low high Va large decrease in incidence result in stall in negative incidence very low ηc Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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**Some Deductions from the Compressor Characteristics**

At high pressure operation Blow-off at an intermediate stage (wasteful). Incidence can be maintained at design value by increasing the speed of last stage (HPC) and decreasing the speed of first stage (LPC); Two spools are mechanically independent but aerodynamically coupled. Me 423 Spring 2006 Prof. Dr. O. Cahit ERALP

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