# Rotordynamic Evaluation of Full Scale Rotor on Tilting Pad Bearings with 0.1 and 0.3 Preload

Authors: Weimin Wang; Qihang Li; Jinji Gao; Feng He; Tim Diamond; Paul Allaire
Journal: Shock and Vibration
 (2014)

---

## Abstract

A system identification method for rotating machinery stability evaluation is investigated based on sine sweep excitation testing with electromagnetic actuator. The traditional MIMO FRF is transformed into dFRF from real number field to complex field with a transformation matrix, eliminating the influence of forward and backward modal overlap and providing higher accuracy to identify rotor’s first forward modal parameters using the rational polynomial method. The modal parameters are acquired for stability estimation. Furthermore, two sets of bearing with preloads of 0.1 and 0.3 under both load-on-pad (LOP) and load-between-pad (LBP) conditions are investigated. The effects of oil inlet pressure (1.0 bar–1.75 bar) and temperature (43°C–51°C) on the stability of rotor are investigated in detail. Results indicate that the stability of rotor will be improved by increasing the oil inlet temperature and pressure. It is found that the rotor is more stable on bearing with 0.1 preload than that of 0.3 preload. Load-on-pad provides more damping to rotor than load-between-pad. The method and outcomes of this paper can provide both theory basis and technology foundation for improving the rotor stability of centrifugal compressors.


---

## Body

## 1. Introduction

Rotordynamic instability is a self-excited vibration phenomenon which can result due to aerodynamic labyrinth seal force, internal friction damping within the shaft, fluid structure interaction, and unbalanced magnetic force. The steadily increased capacity of today’s ethylene, refinery, LNG, and fertilizer plants results in growing demand for larger compressors and more powerful derivers with larger rotating parts than before. This trend shows that it is critically important to optimize the design of rotors, impellers, and journal bearings to improve rotor dynamics stability in the field and to ensure reliable performance during shopping tests. As the tilting pad bearings are the main source of damping to improve the stability of compressors, it is crucial to understand their effects on the reliability of these machines.Since Lund [1] started tilting pad bearing analysis about 50 years ago, API 684 [2], Kocur et al. [3], Diamond et al. [4], and Childs et al. [5] provide excellent historical perspectives of the development of tilting pad bearing analysis. Theoretical work has advanced to include flexibility of the pad and pivot, pad deformation, nonsynchronous behavior, and thermal effects of the fluid. He et al. [6] explored thermoelastohydrodynamic effects on the bearing characteristics such as minimum film thickness, Babbitt temperature, and stiffness and damping coefficients. Nicholas [7] addressed the tilting pad bearing geometric properties and their influence on bearing and rotordynamics with discussion of the advantages and disadvantages of zero preloaded pads and large pad axial length. Some related experimental work at component level was also included by Nicholas to investigate the effects of dynamic parameters on bearing behavior. Childs and Carter [8] presented rotordynamic data for a rocker-pivot tilting-pad bearing with load-on-pad (LOP) configuration for unit loads from 345 to 3101 kPa and speeds from 4 k to 13 k rpm. Frequency effects on the dynamic stiffness coefficients identification were investigated by applying dynamic force excitation over a range of excitation frequencies. Comparing the LOP results to prior measured LBP results for the same bearing, Childs found that K
y
y of the LOP configuration was significantly larger than LBP with higher loads while K
x
x was almost the same for both configurations. Additionally, stiffness orthotropy defined as K
y
y
/
K
x
x was the same for both LOP and LBP, which increased unit loads. Direct damping coefficients C
x
x and C
y
y were shown to be insensitive to changes of either load or speed, in contrast to the predicted C
y
y. Delgado et al. [9] presented the identification of the rotordynamic force coefficients for direct lubricated five-pad and four-pad tilting pad bearings in 2010. The results indicated that the force coefficients of four-pad bearing with load-between-pad configuration show similar coefficients in the loaded and orthogonal directions. On the other hand, as expected, the five-pad bearing load-on-pad shows larger coefficients (25% more) in the loaded direction. More recently, he [10] investigated the dynamic characterization of a five-pad, tilting pad bearing with two pivot offset confirgurations of 0.5 and 0.6. The experiments include the identification of bearing coefficients for different speeds from 2500 to 15000 rpm and two unit loads of 0.4 and 0.8 Mpa in a component level test rig. The results show a relatively small decay of the real part of the dynamic stiffness that is captured with added mass coefficients. On the other hand, the imaginary part of the dynamic impedance shows a linear trend with frequency resulting in a constant damping coefficient.System level bearing dynamic performance tests are also carried out in both the full scale test rig at laboratory level and shop testing of centrifugal compressor under full load full speed condition. Cloud [11] experimentally compared the stability performance of tilting pad bearings with preloads 0.1 and 0.3. The stability threshold dependence on unbalance was tested. Ikeno et al. [12] investigated the difference between load-on-pad (LOP) and load-between-pad (LBP) types on a centrifugal compressor rotor supported by five tilting pads bearings. The dynamic performance difference between five pads and four pads was also investigated. A unique test was presented to measure and compare the oil film profile, pressure, and temperature along the pad surfaces as well as the pad vibration for different types of journal bearings under rotating conditions. The dynamic responses from the experiment were compared with the results from 3D finite element analysis/computational fluid dynamics (FEA/CFD) for each type of bearings. Takahashi et al. [13] identified the bearing coefficients and the API cross-coupled stiffness using test results with unidirectional exciting force. A comparison of the estimated and calculated coefficients showed modes agreement. Delgado et al. [10] carried out system level bearing testing to identify the log decrement of the rotor.The system identification methods for the rotor bearing systems have been investigated by many studies. Cloud [11], Zhong [14] and Pettinato and Cloud [15] used the time domain method. Lee [16], Joh and Lee [17], Kessler and Kim [18], Bidaut et al. [19], and Takahashi et al. [13] investigated the modal parameters and their effects based on frequency domain methods, such as circle fitting, MIMO FRF, and SISO dFRF. Since rotordynamic experimental measurement is often noisy, Dimond et al. [20] employed power spectral density functions and forward and backward whirl orbits to obtain the effective stiffness and damping which are dependent on the excitation frequency.Because of the key role of tilting pad that journal bearing plays in the stability performance of centrifugal compressors [21], the way to identify and predict its characteristic parameters is the focus for many engineers and researchers. In this paper, sine swept vibration excitation using electromagnetic actuator is conducted, and the least square method is applied to estimate the frequency response function (FRF) to improve the data accuracy. Additionally, smoothing process method is used to restrain the high-frequency noise to obtain clear frequency response characteristics. Then, the traditional multiple-input-multiple output frequency response function (MIMO FRF) is transformed into direct frequency response function (dFRF), which eliminates the influence of forward and backward modal superposition and provides data with higher accuracy for the rational polynomial method to identify the system. Finally, the modal parameters of the system are obtained for stability estimation by applying the rational polynomial method to fit and identify the traditional MIMO FRF and dFRF in complex field. Furthermore, two sets of bearing with preloads 0.1 and 0.3 under load-on-pad (LOP) and load-between-pad (LBP) conditions are investigated. Additionally, the effect of oil inlet pressure (1.0 bar–1.75 bar) and temperature (43°C–51°C) on the system stability is investigated in detail. The method and results of this paper provide both theory basis and technology foundation for improving the rotor stability of centrifugal compressors.


## 2. System Identification Method

### 2.1. Dynamic Model of Rotor Bearing System

Figure1 shows multidegrees rotor bearing systems. It can be described by the following differential equation:(1a)
(
[
M
]
s
+
[
M
]
m
)
{
q
¨
}
+
(
[
C
]
b
-
Ω
(
[
G
]
s
+
[
G
]
m
)
)
{
q
˙
}
+
(
[
K
]
s
+
[
K
]
b
+
[
K
]
c
)
{
q
}
=
{
f
(
t
)
}
.Figure 1
Multidegree rotor bearing system.Here, the subscriptionss, m, b, and c represent the shaft, disk (lumped mass), bearing, and cross-coupling effect. [
M
], [
C
], [
G
], and [
K
] are the mass, damping, gyroscopic effect, and stiffness matrix, respectively. {
f
(
t
)
} represents the exciting force including external exciting force such as fluid excitation and internal force such as unbalance force. The force may be either a constant vector or a function of displacement or velocity of rotor vibration. Displacement vector {
q
}, described as {
u
,
v
,
α
,
β
}, includes translational and rotational degree of freedom (DOF). Although this vector has four degrees, it is difficult to measure α and β in the process of modal identification for multidegree rotor bearing systems. Therefore, the two rotational DOF are neglected. At a rotating speed of Ω, (1a) can be reduced
(1b)
[
M
]
q
¨
+
[
C
]
q
˙
+
[
K
]
q
=
f
(
t
)
.Here, displacement responseq
(
t
) can be described as
(1c)
q
(
t
)
=
(
x
(
t
)
y
(
t
)
)
.Excitation forcef
(
t
) can be described as
(1d)
f
(
t
)
=
(
f
x
(
t
)
f
y
(
t
)
)
.Through Fourier transform of (1b), the FRF matrix H
(
j
ω
) can be acquired as follow:
(2)
[
X
(
j
ω
)
Y
(
j
ω
)
]
=
[
H
x
x
H
x
y
H
y
x
H
y
y
]
[
F
x
(
j
ω
)
F
y
(
j
ω
)
]
,
H
m
n
(
j
ω
)
=
∑
i
=
B
,
F
∑
r
=
1
S
N
[
u
v
-
′
j
ω
-
λ
+
u
-
v
′
j
ω
-
λ
]
r
i
(
m
,
n
=
x
,
y
)
.Here,j
=
-
1 and ω is angular frequency. H
m
n is the response in m direction resulting from the excitation force in n direction. F and B represent the forward and backward precession. S
N means the total number of support points. u is modal vector and v is the vector of adjoint matrix. λ is eigenvalue. λ
- is the complex conjugate of λ.


### 2.2. Analysis Model in Real Number Field

An important step for system identification of rotor bearing systems is acquiring the transfer function matrixH
(
j
ω
). Rewriting (2), the MIMO transfer function model can be obtained as (3), which is a coupled system. One set of input and output data is not enough to identify the modal parameters. To solve this problem, rewrite the first item of (3), as (4) shows. Consider the following:
(3)
X
(
j
ω
)
=
H
x
x
F
x
(
j
ω
)
+
H
x
y
F
y
(
j
ω
)
,
Y
(
j
ω
)
=
H
y
x
F
x
(
j
ω
)
+
H
y
y
F
y
(
j
ω
)
,
(4)
[
X
(
j
ω
)
]
=
[
F
x
(
j
ω
)
F
y
(
j
ω
)
]
[
H
x
x
H
x
y
]
.Because the FRF matrix is the inherent properties of rotor bearing system, the relationship between any excitation force and response should satisfy (4). Therefore, two sets of independent input and output data are enough for solving this function. To improve the accuracy of experimental test, several independent tests are needed and can be described(5a)
[
X
(
j
ω
)
I
X
(
j
ω
)
I
I
⋮
X
(
j
ω
)
N
]
=
[
[
F
x
(
j
ω
)
F
y
(
j
ω
)
]
I
[
F
x
(
j
ω
)
F
y
(
j
ω
)
]
I
I
⋮
[
F
x
(
j
ω
)
F
y
(
j
ω
)
]
N
]
[
H
x
x
H
x
y
]
.Here,I
,
I
I
,
…
,
N represent the sequence number of test results. Simplifying this equation gives
(5b)
[
X
]
N
×
1
=
[
F
]
N
×
2
[
H
x
x
H
x
y
]
.Solving this equation, we can get(6a)
[
H
x
x
H
x
y
]
=
[
F
]
N
×
2
+
[
X
]
N
×
1
.From the theory of matrix, (6a) is the minimum norm least squares solution of the FRF coming from the independent test results. It is also called the best approximation solution. By transposing (6a), we can get
(6b)
[
H
x
x
H
x
y
]
=
[
X
]
1
×
N
[
F
]
2
×
N
+
.Based on the same principle, we can get (7) for y direction. Consider the following:
(7)
[
H
y
x
H
y
y
]
=
[
Y
]
1
×
N
[
F
]
2
×
N
+
.Combining (6b) and (7), The FRF matrix H
(
j
ω
) can be achieved as
(8)
[
H
x
x
H
x
y
H
y
x
H
y
y
]
=
[
X
Y
]
2
×
N
[
F
]
2
×
N
+
.Here(9)
[
X
Y
]
2
×
N
=
[
[
X
Y
]
I
[
X
Y
]
I
I
⋯
[
X
Y
]
N
]
,
[
F
]
2
×
N
+
=
[
[
F
x
F
y
]
I
[
F
x
F
y
]
I
I
⋯
[
F
x
F
y
]
N
]
.


### 2.3. Analysis Model in Complex Number Field

Because the gyroscopic effects are usually presented in flexible rotor systems, results of traditional MIMO FRF method include both forward and backward precession modal parameters. This can be concluded from (2). However, the damping ratio of first forward precession modal decides whether it is stable or not. Here we have to separate the forward and backward precession in the complex domain of FRF.To do so, complex displacementr
(
t
) is introduced to describe the displacement signals x
(
t
) and y
(
t
) in real number field as shows the following equation:
(10)
[
r
(
t
)
r
-
(
t
)
]
=
[
1
j
1
-
j
]
[
x
(
t
)
y
(
t
)
]
,
[
f
r
(
t
)
f
-
r
(
t
)
]
=
[
1
j
1
-
j
]
[
f
x
(
t
)
f
y
(
t
)
]
,Here,J
=
[
1
j
1
-
j
] is the transform matrix. r
-
(
t
), f
-
r
(
t
) means the conjugate of r
(
t
), f
r
(
t
), j
=
-
1.FRF in complex field can be described asG
(
j
ω
) as
(11)
[
R
(
j
ω
)
R
-
(
j
ω
)
]
=
[
G
r
r
G
r
r
-
G
r
-
r
G
r
-
r
-
]
[
F
r
(
j
ω
)
F
-
r
(
j
ω
)
]
,
where  R
(
j
ω
) and R
-
(
j
ω
) are the Fourier transform (FT) of r
(
t
) and r
-
(
t
) respectively. Using Fourier transform, (10) can be rewriten as
(12)
[
R
(
j
ω
)
R
-
(
j
ω
)
]
=
J
[
X
(
j
ω
)
Y
(
j
ω
)
]
,
[
F
r
(
j
ω
)
F
-
r
(
j
ω
)
]
=
J
[
F
x
(
j
ω
)
F
y
(
j
ω
)
]
.Combining (2) and (10), we can get
(13)
[
R
(
j
ω
)
R
-
(
j
ω
)
]
=
J
[
H
x
x
H
x
y
H
y
x
H
y
y
]
J
-
1
[
F
r
(
j
ω
)
F
-
r
(
j
ω
)
]
.Here, we can get the relationship between the FRF matrix in real number fieldH
(
j
ω
) and complex number field G
(
j
ω
):
(14)
[
G
r
r
G
r
r
-
G
r
-
r
G
r
-
r
-
]
=
J
[
H
x
x
H
x
y
H
y
x
H
y
y
]
J
-
1
.Here,H
m
n
(
-
j
ω
)
=
H
-
m
n
(
j
ω
) (m
,
n
=
x
,
y). So we can get G
r
r
(
-
j
ω
) through G
(
-
j
ω
)
=
J
H
(
-
j
ω
)
J
-
1.Thus, forward and backward modal are separated. FRF at positive and negative coordinate can be achieved.


### 2.4. Accuracy Verification of the Modal Identification Strategy by Numerical Method

Several modal identification technologies based on prediction error methods (PEM), such as circle fit, least square fitting, and rational fraction polynomial method (RFP), are widely used in industry. RFP method is adapted in this paper because of it high accuracy to identify the traditional MIMO FRF and complex field dFRF. The particular advantage offered by this approach is the possibility of formulating the curve fitting problem as a linear set of equations, thereby making the solution amenable to a direct matrix solution.Figure2 shows a rotordynamic model of a nine-stage centrifugal compressor model composed of 24 beam elements. In this model, mass of the centrifugal impel is represented as lumped mass. Bearing and fluid excitation effect of impeller is represented as general spring with four stiffness and four damping coefficients.Figure 2
Rotordynamic model of a nine-stage centrifugal compressor model.Figure3 indicates the bode plot of the rotor vibration under sine sweep excitation. The exciting force f
(
t
) can be described as
(15)
f
(
t
)
=
(
f
x
(
t
)
f
y
(
t
)
)
=
(
5
cos
⁡
(
ω
t
)
5
sin
(
ω
t
)
)
,
where  ω is the frequency of exciting force ranging from 100 to 1500 rad/sec. The rotating speed of the rotor is 8000 rpm. Amplitude of the vibration in both X and Y directions reaches the peak at 3290 rpm and 3300 rpm. Figure 4 shows the theoretical frequency response curve and the fitted curve based on RFP. Table 1 lists the theoretical and identified natural frequency and log decrement of the rotor based on RFP method. From this we can see that the RFP method has high accuracy.Table 1
Comparison between theoretical and identified result.
Theoretical
Identified result
Deviation
X frequency (rpm)
3290 rpm
3295.02 rpm
0.15326
Y frequency (rpm)
3300 rpm
3294.56 rpm
−0.00165
Log decrementδ
0.13088
0.129923 (X)
−0.00731
0.129629 (Y)
−0.00965Figure 3
Bode plot of the rotor vibration response under sine sweep excitation.Figure 4
Fitted result based on RFP method.


## 2.1. Dynamic Model of Rotor Bearing System

Figure1 shows multidegrees rotor bearing systems. It can be described by the following differential equation:(1a)
(
[
M
]
s
+
[
M
]
m
)
{
q
¨
}
+
(
[
C
]
b
-
Ω
(
[
G
]
s
+
[
G
]
m
)
)
{
q
˙
}
+
(
[
K
]
s
+
[
K
]
b
+
[
K
]
c
)
{
q
}
=
{
f
(
t
)
}
.Figure 1
Multidegree rotor bearing system.Here, the subscriptionss, m, b, and c represent the shaft, disk (lumped mass), bearing, and cross-coupling effect. [
M
], [
C
], [
G
], and [
K
] are the mass, damping, gyroscopic effect, and stiffness matrix, respectively. {
f
(
t
)
} represents the exciting force including external exciting force such as fluid excitation and internal force such as unbalance force. The force may be either a constant vector or a function of displacement or velocity of rotor vibration. Displacement vector {
q
}, described as {
u
,
v
,
α
,
β
}, includes translational and rotational degree of freedom (DOF). Although this vector has four degrees, it is difficult to measure α and β in the process of modal identification for multidegree rotor bearing systems. Therefore, the two rotational DOF are neglected. At a rotating speed of Ω, (1a) can be reduced
(1b)
[
M
]
q
¨
+
[
C
]
q
˙
+
[
K
]
q
=
f
(
t
)
.Here, displacement responseq
(
t
) can be described as
(1c)
q
(
t
)
=
(
x
(
t
)
y
(
t
)
)
.Excitation forcef
(
t
) can be described as
(1d)
f
(
t
)
=
(
f
x
(
t
)
f
y
(
t
)
)
.Through Fourier transform of (1b), the FRF matrix H
(
j
ω
) can be acquired as follow:
(2)
[
X
(
j
ω
)
Y
(
j
ω
)
]
=
[
H
x
x
H
x
y
H
y
x
H
y
y
]
[
F
x
(
j
ω
)
F
y
(
j
ω
)
]
,
H
m
n
(
j
ω
)
=
∑
i
=
B
,
F
∑
r
=
1
S
N
[
u
v
-
′
j
ω
-
λ
+
u
-
v
′
j
ω
-
λ
]
r
i
(
m
,
n
=
x
,
y
)
.Here,j
=
-
1 and ω is angular frequency. H
m
n is the response in m direction resulting from the excitation force in n direction. F and B represent the forward and backward precession. S
N means the total number of support points. u is modal vector and v is the vector of adjoint matrix. λ is eigenvalue. λ
- is the complex conjugate of λ.


## 2.2. Analysis Model in Real Number Field

An important step for system identification of rotor bearing systems is acquiring the transfer function matrixH
(
j
ω
). Rewriting (2), the MIMO transfer function model can be obtained as (3), which is a coupled system. One set of input and output data is not enough to identify the modal parameters. To solve this problem, rewrite the first item of (3), as (4) shows. Consider the following:
(3)
X
(
j
ω
)
=
H
x
x
F
x
(
j
ω
)
+
H
x
y
F
y
(
j
ω
)
,
Y
(
j
ω
)
=
H
y
x
F
x
(
j
ω
)
+
H
y
y
F
y
(
j
ω
)
,
(4)
[
X
(
j
ω
)
]
=
[
F
x
(
j
ω
)
F
y
(
j
ω
)
]
[
H
x
x
H
x
y
]
.Because the FRF matrix is the inherent properties of rotor bearing system, the relationship between any excitation force and response should satisfy (4). Therefore, two sets of independent input and output data are enough for solving this function. To improve the accuracy of experimental test, several independent tests are needed and can be described(5a)
[
X
(
j
ω
)
I
X
(
j
ω
)
I
I
⋮
X
(
j
ω
)
N
]
=
[
[
F
x
(
j
ω
)
F
y
(
j
ω
)
]
I
[
F
x
(
j
ω
)
F
y
(
j
ω
)
]
I
I
⋮
[
F
x
(
j
ω
)
F
y
(
j
ω
)
]
N
]
[
H
x
x
H
x
y
]
.Here,I
,
I
I
,
…
,
N represent the sequence number of test results. Simplifying this equation gives
(5b)
[
X
]
N
×
1
=
[
F
]
N
×
2
[
H
x
x
H
x
y
]
.Solving this equation, we can get(6a)
[
H
x
x
H
x
y
]
=
[
F
]
N
×
2
+
[
X
]
N
×
1
.From the theory of matrix, (6a) is the minimum norm least squares solution of the FRF coming from the independent test results. It is also called the best approximation solution. By transposing (6a), we can get
(6b)
[
H
x
x
H
x
y
]
=
[
X
]
1
×
N
[
F
]
2
×
N
+
.Based on the same principle, we can get (7) for y direction. Consider the following:
(7)
[
H
y
x
H
y
y
]
=
[
Y
]
1
×
N
[
F
]
2
×
N
+
.Combining (6b) and (7), The FRF matrix H
(
j
ω
) can be achieved as
(8)
[
H
x
x
H
x
y
H
y
x
H
y
y
]
=
[
X
Y
]
2
×
N
[
F
]
2
×
N
+
.Here(9)
[
X
Y
]
2
×
N
=
[
[
X
Y
]
I
[
X
Y
]
I
I
⋯
[
X
Y
]
N
]
,
[
F
]
2
×
N
+
=
[
[
F
x
F
y
]
I
[
F
x
F
y
]
I
I
⋯
[
F
x
F
y
]
N
]
.


## 2.3. Analysis Model in Complex Number Field

Because the gyroscopic effects are usually presented in flexible rotor systems, results of traditional MIMO FRF method include both forward and backward precession modal parameters. This can be concluded from (2). However, the damping ratio of first forward precession modal decides whether it is stable or not. Here we have to separate the forward and backward precession in the complex domain of FRF.To do so, complex displacementr
(
t
) is introduced to describe the displacement signals x
(
t
) and y
(
t
) in real number field as shows the following equation:
(10)
[
r
(
t
)
r
-
(
t
)
]
=
[
1
j
1
-
j
]
[
x
(
t
)
y
(
t
)
]
,
[
f
r
(
t
)
f
-
r
(
t
)
]
=
[
1
j
1
-
j
]
[
f
x
(
t
)
f
y
(
t
)
]
,Here,J
=
[
1
j
1
-
j
] is the transform matrix. r
-
(
t
), f
-
r
(
t
) means the conjugate of r
(
t
), f
r
(
t
), j
=
-
1.FRF in complex field can be described asG
(
j
ω
) as
(11)
[
R
(
j
ω
)
R
-
(
j
ω
)
]
=
[
G
r
r
G
r
r
-
G
r
-
r
G
r
-
r
-
]
[
F
r
(
j
ω
)
F
-
r
(
j
ω
)
]
,
where  R
(
j
ω
) and R
-
(
j
ω
) are the Fourier transform (FT) of r
(
t
) and r
-
(
t
) respectively. Using Fourier transform, (10) can be rewriten as
(12)
[
R
(
j
ω
)
R
-
(
j
ω
)
]
=
J
[
X
(
j
ω
)
Y
(
j
ω
)
]
,
[
F
r
(
j
ω
)
F
-
r
(
j
ω
)
]
=
J
[
F
x
(
j
ω
)
F
y
(
j
ω
)
]
.Combining (2) and (10), we can get
(13)
[
R
(
j
ω
)
R
-
(
j
ω
)
]
=
J
[
H
x
x
H
x
y
H
y
x
H
y
y
]
J
-
1
[
F
r
(
j
ω
)
F
-
r
(
j
ω
)
]
.Here, we can get the relationship between the FRF matrix in real number fieldH
(
j
ω
) and complex number field G
(
j
ω
):
(14)
[
G
r
r
G
r
r
-
G
r
-
r
G
r
-
r
-
]
=
J
[
H
x
x
H
x
y
H
y
x
H
y
y
]
J
-
1
.Here,H
m
n
(
-
j
ω
)
=
H
-
m
n
(
j
ω
) (m
,
n
=
x
,
y). So we can get G
r
r
(
-
j
ω
) through G
(
-
j
ω
)
=
J
H
(
-
j
ω
)
J
-
1.Thus, forward and backward modal are separated. FRF at positive and negative coordinate can be achieved.


## 2.4. Accuracy Verification of the Modal Identification Strategy by Numerical Method

Several modal identification technologies based on prediction error methods (PEM), such as circle fit, least square fitting, and rational fraction polynomial method (RFP), are widely used in industry. RFP method is adapted in this paper because of it high accuracy to identify the traditional MIMO FRF and complex field dFRF. The particular advantage offered by this approach is the possibility of formulating the curve fitting problem as a linear set of equations, thereby making the solution amenable to a direct matrix solution.Figure2 shows a rotordynamic model of a nine-stage centrifugal compressor model composed of 24 beam elements. In this model, mass of the centrifugal impel is represented as lumped mass. Bearing and fluid excitation effect of impeller is represented as general spring with four stiffness and four damping coefficients.Figure 2
Rotordynamic model of a nine-stage centrifugal compressor model.Figure3 indicates the bode plot of the rotor vibration under sine sweep excitation. The exciting force f
(
t
) can be described as
(15)
f
(
t
)
=
(
f
x
(
t
)
f
y
(
t
)
)
=
(
5
cos
⁡
(
ω
t
)
5
sin
(
ω
t
)
)
,
where  ω is the frequency of exciting force ranging from 100 to 1500 rad/sec. The rotating speed of the rotor is 8000 rpm. Amplitude of the vibration in both X and Y directions reaches the peak at 3290 rpm and 3300 rpm. Figure 4 shows the theoretical frequency response curve and the fitted curve based on RFP. Table 1 lists the theoretical and identified natural frequency and log decrement of the rotor based on RFP method. From this we can see that the RFP method has high accuracy.Table 1
Comparison between theoretical and identified result.
Theoretical
Identified result
Deviation
X frequency (rpm)
3290 rpm
3295.02 rpm
0.15326
Y frequency (rpm)
3300 rpm
3294.56 rpm
−0.00165
Log decrementδ
0.13088
0.129923 (X)
−0.00731
0.129629 (Y)
−0.00965Figure 3
Bode plot of the rotor vibration response under sine sweep excitation.Figure 4
Fitted result based on RFP method.


## 3. Experimental Identification Process and Result

### 3.1. Description of the Test Rig

To investigate the stability of a flexible rotor supported by tilting pad bearing, one test rig was built in the ROMAC lab [11]. Figure 5 displays the overall rig layout. The test rig is consisted of a 1549.4 mm long rotor supported on two tilting pad journal bearings. Incorporating three AMBs, the test apparatus was mounted to a concrete block separated from its motor drive. Two of the magnet actuators, designated actuators 1 and 2, were located between the journal bearings for the application of cross-coupling and control force. These locations mimic those typical industrial between-bearing machines, where various destabilizing components, such as oil and labyrinth seals, present. The third actuator (called the shaker) was located at the outboard end, where previous industrial stability measurement investigations applied an external excitation. Figure 6 presents the rotor assembly. Figure 7 shows a picture of the bearing assemblies. The pad preload was 0.3 and the assembled clearance of two bearings was maintained at approximately 172.7 microns. Hunter presents the detailed information about this test rig [11].Figure 5
Test rig for stability of rotor supported by tilting pad bearing [11].Figure 6
Rotor assembly in the test rig [11].Figure 7
Drawing of bearing assembly and picture [11].As Figure8 indicates, the damping ratio measurements were carried out by applying a harmonic force with a sweep over a frequency range from 20 Hz to 200 Hz. To avoid any distortion of the measured resonance curves a frequency increase rate of 1 Hz/sec was defined. The level of the excitation force was adjusted in order to ensure high quality responses.Figure 8
Current signal of the magnetic bearing exciter.


### 3.2. Dynamic Characteristic of the Test Rig

In this paper, system identification based on MIMO FRF and SISO dFRF is investigated. Table2 lists the test conditions. Here, the rotating speed is 9000 r/min. By adjusting the amplitude of the exciting force in X and Y directions, five groups tests were carried out and ten sets of data were acquired. For example, in cross-couple excitation 1, X
=
1.0, Y
=
±
0.9, means Y
/
X
=
±
0.9.Table 2
Current coefficient in the experimental test.
Excitation method
X
Y
Excite inX
1.0
0
Excite inY
0
1.0
Forward and backward
1.0
±1.0
Cross-coupling excite 1
1.0
±0.9
Cross-coupling excite 2
1.0
±0.8
Cross-coupling excite 3
1.0
±1.1To have a better insight on the dynamic performance of the test rig, waterfall plot in the rotating speed increase process is provided in Figure9. Here, the preload of the bearing is 0.3. From this we can see that the precession is mainly forward at low speed. As speed increases, the precession direction changes to backward near the critical speed region. Then, the whirl direction changes to be forward again and the vibration amplitude reaches its peak. Meanwhile, we can observe that the vibration is mainly synchronous with a very slight nonsynchronous vibration, which indicates that the test rig is in good state.Figure 9
Waterfull plot in the run up process.Figure10 indicates the full spectrum waterfall of the vibration under forward excitation when rotating at 9000 rpm. That is Y
/
X
=
1 as listed in Table 2. From this we can see that there are three vibration peaks. One of them is backward vibration and the other two are forward vibration. Figure 11 indicates the full spectrum waterfall of the vibration under backward excitation at the same rotating speed. From this we can see that there are also three vibration peaks. But two of them are backward and the other one is forward. This is mainly caused by the anisotropy of the dynamic characteristic of the bearing.Figure 10
Full spectrum waterfalls at forward excitation.Figure 11
Full spectrum waterfalls at backward excitation.


### 3.3. Identification Result Based on MIMO Signal

Figure12 is the FRF characteristic curve of H
x
x according to (8). Figures 12(a)–12(c) are the curve achieved by two, five, and ten times sweep result as Table 2 listed. It can be seen that, with the increase of test times, the FRF curve becomes more and more clear. The accident error in the test process will be depressed by an increase in the number of testing; therefore, the accuracy will be improved. In Figure 12(d), smoothing process method is adopted based on the result of Figure 12(c); it shows that the noise is depressed dramatically.Characteristic curve ofH
x
x.
(a)
Two-times result
(b)
Five-times result
(c)
Ten-times result
(d)
Result after smoothing processTable3 lists the identified damping ratio results using rational fraction polynomial method (RFP) at different test number and different average points number. The test number can be observed to have prominent effect on the result. On the other hand, smoothing process has little effect on the result, although it can depress the noise. This also verifies that the RFP method is not sensitive to the noise of signal.Table 3
Identified damping ratio result under different test number and average points number.
Points number Av
1
5
10
15
Test numberN
2
1.953
1.965
1.970
1.972
5
2.007
2.020
2.023
2.025
8
2.044
2.053
2.055
2.056
10
2.037
2.057
2.037
2.038


### 3.4. Comparison of the Test Result under Different Identification

Figure13 indicates the FRF curve of H
x
x and H
x
y based on MIMO FRF method. Because H
y
x and H
y
y curve have a similar shape, they are not shown in the paper. Here, H
x
x and H
x
y are the combination of several models. Both forward and backward modals are included. Different modals resulting from the anisotropy of bearing dynamic parameters are also included.Test and fitted result based on MIMO FRF.
(a)
H
x
x FRF curve
(b)
H
x
y FRF curveFigure14 shows the FRF curve of G
r
r based on SISO dFRF method in positive and negative frequency fields. According to (14), FRF matrix H in real number field based on MIMO method is transformed to G which is FRF matrix in complex number field. Thus, forward and backward processions are separated. Negative frequency means backward precession and positive frequency means forward precession.Test and fitted result based on SISO dFRF.
(a)
G
r
r
(
-
j
ω
) FRF curve
(b)
G
r
r
(
j
ω
) FRF curveComparing the FRF based on MIMO FRF and SISO dFRF as indicated in Figures13 and 14, respectively, it can be concluded that the traditional MIMO method can lead to modal mixing because it lacks the ability to separate the forward and backward precession. With SISO dFRF method, two peaks emerge in both positive and negative frequency regions. This may result from the anisotropy of bearing dynamic characteristics. It can also be found that the degree of curve fitting based on rational fraction polynomial method (RFP) is better than that using dFRF method.Table4 shows the identified natural frequency and damping ratio based on MIMO FRF and SISO dFRF method. These values correspond to the FRF curve showed in Figures 12 and 13.Table 4
Identified result based on MIMO FRF and SISO dFRF.
MIMO FRF
Frequencyf/Hz
Damping ratio
Frequencyf/Hz
Damping ratio
H
x
x
H
x
y
MIMO FRF
83.98
0.0202
84.09
0.0200
88.91
0.0268
89.06
0.0243
SISO  dFRF
Frequencyf/Hz
Damping ratio
Frequencyf/Hz
Damping ratio
SISO dFRF
−83.81
0.0210
84.08
0.0194
−89.38
0.0237
89.19
0.0259
Note: negative frequency means backward, and positive frequency means forward.


## 3.1. Description of the Test Rig

To investigate the stability of a flexible rotor supported by tilting pad bearing, one test rig was built in the ROMAC lab [11]. Figure 5 displays the overall rig layout. The test rig is consisted of a 1549.4 mm long rotor supported on two tilting pad journal bearings. Incorporating three AMBs, the test apparatus was mounted to a concrete block separated from its motor drive. Two of the magnet actuators, designated actuators 1 and 2, were located between the journal bearings for the application of cross-coupling and control force. These locations mimic those typical industrial between-bearing machines, where various destabilizing components, such as oil and labyrinth seals, present. The third actuator (called the shaker) was located at the outboard end, where previous industrial stability measurement investigations applied an external excitation. Figure 6 presents the rotor assembly. Figure 7 shows a picture of the bearing assemblies. The pad preload was 0.3 and the assembled clearance of two bearings was maintained at approximately 172.7 microns. Hunter presents the detailed information about this test rig [11].Figure 5
Test rig for stability of rotor supported by tilting pad bearing [11].Figure 6
Rotor assembly in the test rig [11].Figure 7
Drawing of bearing assembly and picture [11].As Figure8 indicates, the damping ratio measurements were carried out by applying a harmonic force with a sweep over a frequency range from 20 Hz to 200 Hz. To avoid any distortion of the measured resonance curves a frequency increase rate of 1 Hz/sec was defined. The level of the excitation force was adjusted in order to ensure high quality responses.Figure 8
Current signal of the magnetic bearing exciter.


## 3.2. Dynamic Characteristic of the Test Rig

In this paper, system identification based on MIMO FRF and SISO dFRF is investigated. Table2 lists the test conditions. Here, the rotating speed is 9000 r/min. By adjusting the amplitude of the exciting force in X and Y directions, five groups tests were carried out and ten sets of data were acquired. For example, in cross-couple excitation 1, X
=
1.0, Y
=
±
0.9, means Y
/
X
=
±
0.9.Table 2
Current coefficient in the experimental test.
Excitation method
X
Y
Excite inX
1.0
0
Excite inY
0
1.0
Forward and backward
1.0
±1.0
Cross-coupling excite 1
1.0
±0.9
Cross-coupling excite 2
1.0
±0.8
Cross-coupling excite 3
1.0
±1.1To have a better insight on the dynamic performance of the test rig, waterfall plot in the rotating speed increase process is provided in Figure9. Here, the preload of the bearing is 0.3. From this we can see that the precession is mainly forward at low speed. As speed increases, the precession direction changes to backward near the critical speed region. Then, the whirl direction changes to be forward again and the vibration amplitude reaches its peak. Meanwhile, we can observe that the vibration is mainly synchronous with a very slight nonsynchronous vibration, which indicates that the test rig is in good state.Figure 9
Waterfull plot in the run up process.Figure10 indicates the full spectrum waterfall of the vibration under forward excitation when rotating at 9000 rpm. That is Y
/
X
=
1 as listed in Table 2. From this we can see that there are three vibration peaks. One of them is backward vibration and the other two are forward vibration. Figure 11 indicates the full spectrum waterfall of the vibration under backward excitation at the same rotating speed. From this we can see that there are also three vibration peaks. But two of them are backward and the other one is forward. This is mainly caused by the anisotropy of the dynamic characteristic of the bearing.Figure 10
Full spectrum waterfalls at forward excitation.Figure 11
Full spectrum waterfalls at backward excitation.


## 3.3. Identification Result Based on MIMO Signal

Figure12 is the FRF characteristic curve of H
x
x according to (8). Figures 12(a)–12(c) are the curve achieved by two, five, and ten times sweep result as Table 2 listed. It can be seen that, with the increase of test times, the FRF curve becomes more and more clear. The accident error in the test process will be depressed by an increase in the number of testing; therefore, the accuracy will be improved. In Figure 12(d), smoothing process method is adopted based on the result of Figure 12(c); it shows that the noise is depressed dramatically.Characteristic curve ofH
x
x.
(a)
Two-times result
(b)
Five-times result
(c)
Ten-times result
(d)
Result after smoothing processTable3 lists the identified damping ratio results using rational fraction polynomial method (RFP) at different test number and different average points number. The test number can be observed to have prominent effect on the result. On the other hand, smoothing process has little effect on the result, although it can depress the noise. This also verifies that the RFP method is not sensitive to the noise of signal.Table 3
Identified damping ratio result under different test number and average points number.
Points number Av
1
5
10
15
Test numberN
2
1.953
1.965
1.970
1.972
5
2.007
2.020
2.023
2.025
8
2.044
2.053
2.055
2.056
10
2.037
2.057
2.037
2.038


## 3.4. Comparison of the Test Result under Different Identification

Figure13 indicates the FRF curve of H
x
x and H
x
y based on MIMO FRF method. Because H
y
x and H
y
y curve have a similar shape, they are not shown in the paper. Here, H
x
x and H
x
y are the combination of several models. Both forward and backward modals are included. Different modals resulting from the anisotropy of bearing dynamic parameters are also included.Test and fitted result based on MIMO FRF.
(a)
H
x
x FRF curve
(b)
H
x
y FRF curveFigure14 shows the FRF curve of G
r
r based on SISO dFRF method in positive and negative frequency fields. According to (14), FRF matrix H in real number field based on MIMO method is transformed to G which is FRF matrix in complex number field. Thus, forward and backward processions are separated. Negative frequency means backward precession and positive frequency means forward precession.Test and fitted result based on SISO dFRF.
(a)
G
r
r
(
-
j
ω
) FRF curve
(b)
G
r
r
(
j
ω
) FRF curveComparing the FRF based on MIMO FRF and SISO dFRF as indicated in Figures13 and 14, respectively, it can be concluded that the traditional MIMO method can lead to modal mixing because it lacks the ability to separate the forward and backward precession. With SISO dFRF method, two peaks emerge in both positive and negative frequency regions. This may result from the anisotropy of bearing dynamic characteristics. It can also be found that the degree of curve fitting based on rational fraction polynomial method (RFP) is better than that using dFRF method.Table4 shows the identified natural frequency and damping ratio based on MIMO FRF and SISO dFRF method. These values correspond to the FRF curve showed in Figures 12 and 13.Table 4
Identified result based on MIMO FRF and SISO dFRF.
MIMO FRF
Frequencyf/Hz
Damping ratio
Frequencyf/Hz
Damping ratio
H
x
x
H
x
y
MIMO FRF
83.98
0.0202
84.09
0.0200
88.91
0.0268
89.06
0.0243
SISO  dFRF
Frequencyf/Hz
Damping ratio
Frequencyf/Hz
Damping ratio
SISO dFRF
−83.81
0.0210
84.08
0.0194
−89.38
0.0237
89.19
0.0259
Note: negative frequency means backward, and positive frequency means forward.


## 4. Factors Affecting the Performance Rotor Bearing System

### 4.1. Influence of the Rotating Speed

Because the rotordynamic instability mainly occurs in high speed turbomachinery, it is necessary to investigate the effect of speed on the stability of the rotor. As Figure15 indicates, the damping ratio decreases with the increase of rotating speed. Four curves, which are based on 0.1 and 0.3 preload, load-between-pad, and load-on-pad, respectively, were provided. The results show that the rotor supported on 0.1 preload bearing has high stability than that of 0.3 preload. The LOP configuration can also be found to give more damping than that with the LBP load configuration, and the difference between LBP and LOP is more distinguishable for 0.1 preload than that of 0.3 preload.Figure 15
The influence of rotating speed on the stability of rotor.When a pad is preloaded, a converging film section exists and the pad will produce hydrodynamic force even if the bearing load approaches zero. As preload decreases, the damping increases, but the stiffness remains approximately constant. Both of these trends result in the increase of the effective damping. Loads between pads provide more symmetric stiffness and damping coefficients, while, the direct stiffness and damping coefficients approach extreme asymmetry as the Sommerfeld number decreases for the load-on-pad case. For load-between-pad these coefficients are very close for the entire Sommerfeld number range. Symmetric supports provide circular orbits, while asymmetric supports cause the elliptical orbit. From the point of vibration amplitude, circular orbits are preferable, since their vibration amplitude is smaller when going through a critical speed compared to the major axis of an elliptical orbit. So elliptical orbit can increase the effective damping of bearings. For the bearing with preload 0.3, the damping ratio of the rotor bearing system is small. So it is not affected prominently between LOP and LBP.


### 4.2. Temperature with the Increase of Speed

High speed rotating machine is always accompanied with high pad temperature. In this test rig, there are four thermal couples in each bearing to detect the pad temperature. Their positions in the pad are Tem1, Tem2, Tem3, and Tem4 as shown in Figure16(a). Here, the oil inlet temperature is 42°C. Figures 16(b)–16(d) indicate the temperature of pad as the increase of rotating speed at four different cases. From this we can see that the relationship between temperature and rotating speed is nearly linear. The maximum temperature in these four cases is nearly the same. Thus, it can be concluded that the preload and load position do not affect the temperature too much.The effect of rotating speed on the temperature of pad.
(a)
Temperature sensor in the tilting pad bearing
(b)
0.1 preload LOP
(c)
0.1 preload LBP (provide later)
(d)
0.3 preload LOP
(e)
0.3 preload LBP


### 4.3. Effect of Oil Inlet Temperature on the Stability of Rotor

Field operation experiences tell us that the emergency shutdown resulting from instability, usually caused by the fluctuation of oil inlet temperature. Also, sometimes the stability of rotor can be improved by controlling the temperature. Figure17 indicates the damping ratio of four types of bearing at different oil inlet pressure. The figure shows that the damping ratio increases with the increase of oil inlet temperature. Bearing with 0.1 preload and LOP is affected more than the three other types.Effect of oil inlet temperature on the stability of rotor.
(a)
0.1 preload LOP
(b)
0.1 preload LBP
(c)
0.3 preload LOP
(d)
0.3 preload LBPUnder the experimental conditions carried out in this paper, the viscosity of oil will decrease with the increase of oil inlet temperature. The stiffness and damping of oil film will both decrease for this reason. However, the decrease of stiffness will increase the effectiveness of damping. So the modal damping of the whole rotor bearing system will increase with the increase of oil inlet temperature. The bearing with 0.1 preload and LOP has the highest damping ratio. So it is more strongly affected by these parameters.


### 4.4. Effect of Oil Inlet Pressure on Stability of Rotor

Similar to the oil inlet temperature, oil inlet pressure is another controllable parameter in field operation. Figure18 indicates that the damping ratio increases with the oil inlet pressure, which shows the improvement of rotor stability. Combining the effect of both oil inlet temperature and pressure, three dimensional figure as Figure 19 can be achieved. From these, we can see that rotors supported by bearing with 0.1 preload have better stability than that with 0.3 preload and Load-on-Pad bearing can provide more damping to rotor than load-between-pad.Effect of oil inlet temperature on the stability of rotor.
(a)
0.1 preload LOP
(b)
0.1 preload LBP
(c)
0.3 preload LOP
(d)
0.3 preload LBPCombination effect of oil inlet and pressure on the stability of rotor.
(a)
(b)
(c)
(d)For the tilting pads bearing, the oil inlet pressure increase does not affect the oil film stiffness significantly. However, the increase of oil inlet pressure will decrease the cavitation region in oil film. This will make the oil film provide more damping for the rotor bearing system. Therefore, the stability of the rotor will be improved by increasing the oil inlet pressure.


## 4.1. Influence of the Rotating Speed

Because the rotordynamic instability mainly occurs in high speed turbomachinery, it is necessary to investigate the effect of speed on the stability of the rotor. As Figure15 indicates, the damping ratio decreases with the increase of rotating speed. Four curves, which are based on 0.1 and 0.3 preload, load-between-pad, and load-on-pad, respectively, were provided. The results show that the rotor supported on 0.1 preload bearing has high stability than that of 0.3 preload. The LOP configuration can also be found to give more damping than that with the LBP load configuration, and the difference between LBP and LOP is more distinguishable for 0.1 preload than that of 0.3 preload.Figure 15
The influence of rotating speed on the stability of rotor.When a pad is preloaded, a converging film section exists and the pad will produce hydrodynamic force even if the bearing load approaches zero. As preload decreases, the damping increases, but the stiffness remains approximately constant. Both of these trends result in the increase of the effective damping. Loads between pads provide more symmetric stiffness and damping coefficients, while, the direct stiffness and damping coefficients approach extreme asymmetry as the Sommerfeld number decreases for the load-on-pad case. For load-between-pad these coefficients are very close for the entire Sommerfeld number range. Symmetric supports provide circular orbits, while asymmetric supports cause the elliptical orbit. From the point of vibration amplitude, circular orbits are preferable, since their vibration amplitude is smaller when going through a critical speed compared to the major axis of an elliptical orbit. So elliptical orbit can increase the effective damping of bearings. For the bearing with preload 0.3, the damping ratio of the rotor bearing system is small. So it is not affected prominently between LOP and LBP.


## 4.2. Temperature with the Increase of Speed

High speed rotating machine is always accompanied with high pad temperature. In this test rig, there are four thermal couples in each bearing to detect the pad temperature. Their positions in the pad are Tem1, Tem2, Tem3, and Tem4 as shown in Figure16(a). Here, the oil inlet temperature is 42°C. Figures 16(b)–16(d) indicate the temperature of pad as the increase of rotating speed at four different cases. From this we can see that the relationship between temperature and rotating speed is nearly linear. The maximum temperature in these four cases is nearly the same. Thus, it can be concluded that the preload and load position do not affect the temperature too much.The effect of rotating speed on the temperature of pad.
(a)
Temperature sensor in the tilting pad bearing
(b)
0.1 preload LOP
(c)
0.1 preload LBP (provide later)
(d)
0.3 preload LOP
(e)
0.3 preload LBP


## 4.3. Effect of Oil Inlet Temperature on the Stability of Rotor

Field operation experiences tell us that the emergency shutdown resulting from instability, usually caused by the fluctuation of oil inlet temperature. Also, sometimes the stability of rotor can be improved by controlling the temperature. Figure17 indicates the damping ratio of four types of bearing at different oil inlet pressure. The figure shows that the damping ratio increases with the increase of oil inlet temperature. Bearing with 0.1 preload and LOP is affected more than the three other types.Effect of oil inlet temperature on the stability of rotor.
(a)
0.1 preload LOP
(b)
0.1 preload LBP
(c)
0.3 preload LOP
(d)
0.3 preload LBPUnder the experimental conditions carried out in this paper, the viscosity of oil will decrease with the increase of oil inlet temperature. The stiffness and damping of oil film will both decrease for this reason. However, the decrease of stiffness will increase the effectiveness of damping. So the modal damping of the whole rotor bearing system will increase with the increase of oil inlet temperature. The bearing with 0.1 preload and LOP has the highest damping ratio. So it is more strongly affected by these parameters.


## 4.4. Effect of Oil Inlet Pressure on Stability of Rotor

Similar to the oil inlet temperature, oil inlet pressure is another controllable parameter in field operation. Figure18 indicates that the damping ratio increases with the oil inlet pressure, which shows the improvement of rotor stability. Combining the effect of both oil inlet temperature and pressure, three dimensional figure as Figure 19 can be achieved. From these, we can see that rotors supported by bearing with 0.1 preload have better stability than that with 0.3 preload and Load-on-Pad bearing can provide more damping to rotor than load-between-pad.Effect of oil inlet temperature on the stability of rotor.
(a)
0.1 preload LOP
(b)
0.1 preload LBP
(c)
0.3 preload LOP
(d)
0.3 preload LBPCombination effect of oil inlet and pressure on the stability of rotor.
(a)
(b)
(c)
(d)For the tilting pads bearing, the oil inlet pressure increase does not affect the oil film stiffness significantly. However, the increase of oil inlet pressure will decrease the cavitation region in oil film. This will make the oil film provide more damping for the rotor bearing system. Therefore, the stability of the rotor will be improved by increasing the oil inlet pressure.


## 5. Summary

System identification method of rotating machinery stability is investigated based on sine sweep excitation experiment with electromagnetic actuator. The least square method is applied to estimate the FRF to improve the data accuracy. Additionally, Smoothing process method is used to restrain the high-frequency noise to obtain clearly the frequency response characteristic. Then, the traditional MIMO FRF is transformed into dFRF from real number field to complex field with a transformation matrix, which eliminates the influence of forward and backward modal overlap and provides higher accuracy data for the rational polynomial method to identify rotor’s first forward modal parameters. Finally, the modal parameters are acquired for stability estimation by applying the rational polynomial method to fit and identify the traditional MIMO FRF and dFRF on complex field. Furthermore, two sets of bearings with preloads 0.1 and 0.3 under load-on-pad (LOP) and load-between-pad (LBP) conditions are investigated, respectively. The effects of oil inlet pressure (1.0 bar–1.75 bar) and temperature (43°C–51°C) on the stability of rotor are investigated in detail. Under the test conditions carried out in this paper, the following phenomena were observed: (1) the stability of rotor is improved by increasing the oil inlet temperature and/or pressure; (2) rotor supported by bearing with 0.1 preload has better stability than that with 0.3 preload; (3) load-on-pad bearing provides more damping than load-between-pad. The method and outcomes of this paper provide both theory basis and technology foundation to improve the rotor stability of centrifugal compressors.



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*Source: 314892-2014-02-20.xml*