# Design Method for Channel Diffusers of Centrifugal Compressors

Authors: Mykola Kalinkevych; Andriy Skoryk
Journal: International Journal of Rotating Machinery
 (2013)

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## Abstract

The design method for channel diffusers of centrifugal compressors, which is based on the solving of the inverse problem of gas dynamics, is presented in the paper. The concept of the design is to provide high pressure recovery of the diffuser by assuming the preseparation condition of the boundary layer along one of the channel surfaces. The channel diffuser was designed with the use of developed method to replace the vaned diffuser of the centrifugal compressor model stage. The numerical simulation of the diffusers was implemented by means of CFD software. Obtained gas dynamic characteristics of the designed diffuser were compared to the base vaned diffuser of the compressor stage.


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## Body

## 1. Introduction

The operating conditions and purpose of centrifugal compressor should be taken into account when choosing the type of its diffuser. Channel diffusers (CD) could be more preferable as compared to other types in the following cases: (1) at small flow angles at the diffuser inlet; (2) when the gas passes from the diffuser channels to the separated cameras; (3) if the diffuser channels turn to the channels of the return element of compressor.Traditional geometry of channel diffusers includes the initial section shaped as a logarithmic spiral along one of the vane surfaces and the main section with straight walls (Figure1(a)). The channel diffusers with wedge vanes are also widely used (Figure 1(b)).Channel diffusers of traditional geometry: (a) channel diffuser with initial section shaped as a logarithmic spiral, (b) channel diffuser with wedge vanes.
(a)
(b)Some authors recommend using the Reneau et al. [1] and Runstadler Jr. and Dean Jr. [2] database for the flat plane diffusers to design wedge-shaped channel diffusers. Kano et al. [3] and Clements and Artt [4] indicated that such data cannot be used to design the high-performance diffuser of centrifugal compressor because of the distorted three-dimensional swirled flow at the inlet. In addition, such a database does not cover the wide range of geometries and inlet flow conditions.Generally, the most effective vane geometry may be obtained by solving the inverse problem of gas dynamics. The maximum pressure rise in diffuser may be achieved when the flow is close to separation. Stratford [5] obtained experimentally the flow with stable preseparation condition of the boundary layer along one of the surfaces of the two-dimensional diffuser. It was shown that, by specifying the preseparation pressure distribution, the required pressure rise may be attained in the shortest possible distance and with the least possible dissipation of energy for a given diffuser dimensions and initial boundary layer. Such approach was later used by Liebeck [6] for estimation of the shape of high lift airfoil and by Hobbs and Weingold [7] for designing the high performance axial compressor airfoils. However, there is no information in applying the preseparation velocity (or pressure) distributions for the design of centrifugal compressor cascades with radial swirled flow.Kalinkevych et al. [8] showed that efficiency of the vaned diffuser (VD) of centrifugal compressor may be improved by using such a concept. In this work the center line shape of the vanes with constant thickness was obtained by defining the preseparation velocity distribution along the pressure surface of the vane.The principles of design method for high-performance channel diffusers (CD) of centrifugal compressors, in which vane thickness increases along the radius, are presented in the paper.


## 2. Design Method

According to the presented method, the diffuser design is based on assuming the preseparation condition of the boundary layer along one of the vane surfaces. Mathematical model for solving the inverse problem of gas dynamics is developed for the steady adiabatic gas flow without separations.The angular momentum change about axisz for the annular element of gas with width Δb and mass flow rate Δm- from the diffuser inlet rin to the current section r (Figure 2) is as follows:
(1)ΔM=Δm-·(rin·cin·cosαin-r·c·cosα).
Moment of forces acting on the zv vanes of diffuser from rin to r is as follows:
(2)ΔM=Δb·zv·∫rinrΔp·r·dr.
Continuity equation is of the form
(3)Δm-=cr·ρ·2π·r·Δb·τ.
Equations (1), (2), and (3) may be represented using gas dynamics relations for isentropic flow:
(4)rin·λin·cosαin-r·λ·cosα=b·zv·pin*m-·acr·∫rinr[π(λps)-π(λss)]·r·dr,m-=λ·ε(λ)·acr·ρ*·2π·r·b·τ·sinα,
where λ, λps, and λss (acr=(2γ/(γ+1))RT* is the critical velocity) are the mean flow velocity within the diffuser channel, velocity along the pressure surface, and velocity along the suction surface of the vane, respectively and α is the mean flow angle within the diffuser channel.Figure 2
Channel diffuser scheme.Pressure and density relations are determined as a function of velocity:(5)π(λ)=pp*=(1-γ-1γ+1·λ2)γ/(γ-1),ε(λ)=ρρ*=(1-γ-1γ+1·λ2)1/(γ-1).
The blockage factor is given by the following equation:
(6)τ=1-δ′·zv2π·r·sinα,
where δ′=δv+∑δ* is the modified vane thickness; δv is vane thickness, and ∑δ* is total displacement thickness of boundary layers in the vane channel estimated using the Loitcyanskii method [9].Velocity distribution, which provides the preseparation condition of the boundary layer along the pressure surface of the vane, is defined by the formula [8]:
(7)λps=λ1·[1+(l--l-1)·(2+Hs)·(-fs)δ-1**]-1/(2+Hs).
Parameters marked with subscript “1” are the coefficients, which affect the given velocity distribution quantitatively.The set of (4) includes unknowns λ, δv, and λss. The dependence α=f(r) may be given as linear.For linear pressure distribution along the vane pitch the relation between the velocities may be defined as(8)π(λps)+π(λss)=2·π(λ).
By substituting equation (8) into equation (4), equation (4) can be solved using numerical methods for numerical integration and root finding.The initial data for the design are(i)
gas properties (R,γ,ν);(ii)
static pressurepin and static temperature Tin at diffuser inlet;(iii)
inlet and outlet flow angles (αin,αout);(iv)
mass flow rate;(v)
geometrics of the meridional contour;(vi)
quantity of vaneszv;(vii)
mean flow angle distribution along the diffuser channel (α=f(r)).As a result of calculation, the vane thickness distribution along the radius δv=f(r) is estimated, so the geometry of the vane is totally defined.The compressor design point flow parameters at the impeller exit are used as mentioned in above initial data for the diffuser design. Presented design method is valid for the subsonic flow along the entire diffuser.


## 3. Application of the Design Method for the Centrifugal Compressor Model Stage

Using presented method, the CD for the model centrifugal compressor stage of JSC “Sumy Frunze NPO” was designed. The design was implemented for the parameters at the diffuser inlet at the design point of the stage. The parameters of the flow were obtained by numerical simulation of the base model compressor stage with VD.The values of design parameters are shown in Table1. The meridional contour geometry, inlet and outlet angles of the vanes are the same as for the base VD.Table 1
Initial data for channel diffuser design.
Design parameter
Value
Pressure at the diffuser inlet, Pa
118000
Temperature at the diffuser inlet, K
319
Mass flow rate, kg/s
1.775
Quantity of vanes
17
Inlet radius,r3, m
0.2622
Outlet radius,r4, m
0.3092
Width of diffuser,b3, m
0.0155
Vane leading edge thickness, m
0.003
Vane leading edge centerline angle,α3v, °
22
Vane trailing edge centerline angle,α4v, °
37The given velocity distribution for the CD design is shown in Figure3. The geometry parameters of the vane are shown in Figure 4. Vane thickness distribution was obtained as a result of design calculation.Figure 3
Given velocity distribution for the channel diffuser design.Vane thickness and angle distribution for the designed channel diffuser.The relative radius in Figures3 and 4 is defined by formula
(9)r-i=ri-rinrout-rin.
The comparison between the vane channels of the base VD and designed CD is shown in Figure 5.Figure 5
The comparison between the base VD vane channel (black) and designed CD vane channel (red).


## 4. Numerical Simulation

Numerical simulation was performed by use of commercial CFD software ANSYS CFX v.14 for two different compressor stages. The first one is the model compressor stage of JSC “Sumy Frunze NPO” with base VD. The second stage has the same impeller as the first. The only difference is the diffuser, which was designed using presented method (see Section3).


### 4.1. Grid Quality and Preprocessor Setup

The steady-state model and high resolution discretization scheme were used for simulations. SST-turbulence model is the most acceptable model for the centrifugal compressor flow simulations [10], which in the case of sufficient grid refinement shows appropriate results for the near-wall boundary layers and flow core.The structured hexahedral grids for impeller and diffusers were created in ANSYS TurboGrid. While creating the near-wall prismatic layers, it was checked that value ofy+ is less than 2. The quantity of grid points within the boundary layers was no less than 20. The coarser grid was created for the flow core, which is acceptable for the SST-turbulence model. The impeller grid consists of 690 690 elements (Figure 6(a)). The CD grid consists of 637 296 elements (Figure 6(b)), and VD grid (Figure 6(c)) consists of 618 618 elements. Due to the differences in geometry of these diffusers, it is not possible to create totally topologically identical grids. The parameters which define the topology of the near-wall prismatic layers and the quantity of grid elements in meridional plane were identical. Therefore this topological difference is acceptable for the comparison. The difference is only in the flow core elements quantity.Grids of the stage elements.
(a)
Impeller
(b)
Channel diffuser
(c)
Vaned diffuserThe main parameters specified in ANSYS CFX preprocessor are shown in Table2. To connect the respective surfaces of the impeller and diffuser, the interface “stage” was used. This type of interface is usually used for the steady state calculations; the parameters at the interface surfaces are averaged circumferentially. Therefore interface “stage” is oriented for estimating of the integral characteristics of the compressor stage.Table 2
Boundary conditions and models, specified in ANSYS CFX preprocessor.
Boundary or model
Option
Impeller inlet
Total pressure, total temperature
Diffuser outlet
Mass flow rate
Interface type between impeller and diffuser
Stage
Turbulence model
SST
Heat transfer model
Total energy
Fluid model
Air ideal gas
Wall heat transfer model
AdiabaticAs the convergence criteria, the discrepancy in static pressure recovery coefficient equal to 0.01 and in total pressure loss coefficient equal to 0.005 has been used.The grid independence study showed that for the design point the diffusers’ nondimensional characteristics change is distinct for the diffusers node quantity less than 400 000. For off-design conditions the results of simulation are more grid-sensitive.The main purpose of simulations was to establish the more effective diffuser by comparing their nondimensional characteristics. Generated grids were indicated as sufficient for such calculations.To evaluate the diffuser aerodynamic performance, the pressure recovery coefficient(10)Cp=pout-pinpin*-pin
and total pressure loss coefficient
(11)ζ=pin*-pout*pin*-pin
were used.


### 4.2. Simulation Results

Obtained nondimensional diffusers’ characteristics are shown in Figure7 as a function of incidence angle
(12)i3=α3v-α3,
where α3v is vane centerline angle at the diffuser inlet.Figure 7
Nondimensional characteristics of designed CD and base VD.It can be seen that characteristics of CD are better than of VD at the range of positive incidence angles. Moreover, maximal value of pressure recovery of CD is slightly higher than of VD. The shape of characteristics of CD is more flat, especially for the total pressure loss coefficient. In order to understand these results the flow pattern within the diffusers was examined.Figure8 presents the velocity vectors within both diffusers for i3≈4°. Predicted high loss level and low pressure recovery of VD occur due to the wide flow separation region. Due to the high pressure gradients, the flow separation occurs on the suction surface of the vane and covers the area from the hub side to midspan. Reducing the effective area resulted in low pressure recovery.Velocity vectors for different flow surfaces of VD (top) and CD (bottom) ati3≈4°.
(a)
Hub side
(b)
MidspanThe flow pattern within the CD is more favorable due to the controlled flow deceleration provided by the designed vane geometry. For the operating conditions range ofi3≈0°–4°, the total losses include only the friction loss and wake mixing loss at diffuser outlet (Figures 8 and 9). Therefore the shape of the loss characteristic of CD is almost straight.Figure 9
Velocity vectors for the midspan plane of VD (top) and CD (bottom) ati3≈1°.As it can be seen from Figure7 for the top pressure recovery operating condition of VD at i3≈1°, the pressure recovery of CD is slightly lower, whereas the losses are practically the same. The flow separation within the CD was detected at i3≈5°.


## 4.1. Grid Quality and Preprocessor Setup

The steady-state model and high resolution discretization scheme were used for simulations. SST-turbulence model is the most acceptable model for the centrifugal compressor flow simulations [10], which in the case of sufficient grid refinement shows appropriate results for the near-wall boundary layers and flow core.The structured hexahedral grids for impeller and diffusers were created in ANSYS TurboGrid. While creating the near-wall prismatic layers, it was checked that value ofy+ is less than 2. The quantity of grid points within the boundary layers was no less than 20. The coarser grid was created for the flow core, which is acceptable for the SST-turbulence model. The impeller grid consists of 690 690 elements (Figure 6(a)). The CD grid consists of 637 296 elements (Figure 6(b)), and VD grid (Figure 6(c)) consists of 618 618 elements. Due to the differences in geometry of these diffusers, it is not possible to create totally topologically identical grids. The parameters which define the topology of the near-wall prismatic layers and the quantity of grid elements in meridional plane were identical. Therefore this topological difference is acceptable for the comparison. The difference is only in the flow core elements quantity.Grids of the stage elements.
(a)
Impeller
(b)
Channel diffuser
(c)
Vaned diffuserThe main parameters specified in ANSYS CFX preprocessor are shown in Table2. To connect the respective surfaces of the impeller and diffuser, the interface “stage” was used. This type of interface is usually used for the steady state calculations; the parameters at the interface surfaces are averaged circumferentially. Therefore interface “stage” is oriented for estimating of the integral characteristics of the compressor stage.Table 2
Boundary conditions and models, specified in ANSYS CFX preprocessor.
Boundary or model
Option
Impeller inlet
Total pressure, total temperature
Diffuser outlet
Mass flow rate
Interface type between impeller and diffuser
Stage
Turbulence model
SST
Heat transfer model
Total energy
Fluid model
Air ideal gas
Wall heat transfer model
AdiabaticAs the convergence criteria, the discrepancy in static pressure recovery coefficient equal to 0.01 and in total pressure loss coefficient equal to 0.005 has been used.The grid independence study showed that for the design point the diffusers’ nondimensional characteristics change is distinct for the diffusers node quantity less than 400 000. For off-design conditions the results of simulation are more grid-sensitive.The main purpose of simulations was to establish the more effective diffuser by comparing their nondimensional characteristics. Generated grids were indicated as sufficient for such calculations.To evaluate the diffuser aerodynamic performance, the pressure recovery coefficient(10)Cp=pout-pinpin*-pin
and total pressure loss coefficient
(11)ζ=pin*-pout*pin*-pin
were used.


## 4.2. Simulation Results

Obtained nondimensional diffusers’ characteristics are shown in Figure7 as a function of incidence angle
(12)i3=α3v-α3,
where α3v is vane centerline angle at the diffuser inlet.Figure 7
Nondimensional characteristics of designed CD and base VD.It can be seen that characteristics of CD are better than of VD at the range of positive incidence angles. Moreover, maximal value of pressure recovery of CD is slightly higher than of VD. The shape of characteristics of CD is more flat, especially for the total pressure loss coefficient. In order to understand these results the flow pattern within the diffusers was examined.Figure8 presents the velocity vectors within both diffusers for i3≈4°. Predicted high loss level and low pressure recovery of VD occur due to the wide flow separation region. Due to the high pressure gradients, the flow separation occurs on the suction surface of the vane and covers the area from the hub side to midspan. Reducing the effective area resulted in low pressure recovery.Velocity vectors for different flow surfaces of VD (top) and CD (bottom) ati3≈4°.
(a)
Hub side
(b)
MidspanThe flow pattern within the CD is more favorable due to the controlled flow deceleration provided by the designed vane geometry. For the operating conditions range ofi3≈0°–4°, the total losses include only the friction loss and wake mixing loss at diffuser outlet (Figures 8 and 9). Therefore the shape of the loss characteristic of CD is almost straight.Figure 9
Velocity vectors for the midspan plane of VD (top) and CD (bottom) ati3≈1°.As it can be seen from Figure7 for the top pressure recovery operating condition of VD at i3≈1°, the pressure recovery of CD is slightly lower, whereas the losses are practically the same. The flow separation within the CD was detected at i3≈5°.


## 5. Conclusions

The numerical simulation showed the potential availability of the developed channel diffuser design method for the high-performance centrifugal compressor design. Efficiency of the compressor stage may be improved at the range of low mass flow rates because of the flow separation prevention and friction area decrease in the channel diffuser.The channel diffusers’ characteristics are more flat and stable for the positive incidence angles as compared to the vaned diffuser.At the further stage of the research, the designed channel diffuser will be tested in detail to verify the real advantages of such diffuser and validation of proposed design method.



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