CN212428959U - Four-support high-speed rotor system formed by elliptical pad bearing and tilting pad bearing - Google Patents
Four-support high-speed rotor system formed by elliptical pad bearing and tilting pad bearing Download PDFInfo
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- CN212428959U CN212428959U CN202020428976.XU CN202020428976U CN212428959U CN 212428959 U CN212428959 U CN 212428959U CN 202020428976 U CN202020428976 U CN 202020428976U CN 212428959 U CN212428959 U CN 212428959U
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Abstract
The utility model discloses a four-support high-speed rotor system formed by an elliptical pad bearing and a tilting pad bearing, which comprises an axial flow compressor rotor and a tail gas turbine rotor which are connected by a rigid coupling; a first elliptical tile bearing is installed on the exhaust side of the axial flow compressor rotor, and a second elliptical tile bearing is installed on the air inlet side of the axial flow compressor rotor; a first tilting pad bearing is arranged on the exhaust side of the tail gas turbine rotor, and a second tilting pad bearing is arranged on the air inlet side of the tail gas turbine rotor; and a shared thrust disc is arranged on the rigid coupling. The two rotors are mutually coupled and damped, the vibration amplitude is reduced, the amplification factor of a damping unbalance response curve corresponding to the critical rotating speed near the working rotating speed of the whole rotor system is smaller than 2.5, and the critical rotating speed is in a critical damping state, so that the dynamic design requirement of the rotor system is met.
Description
Technical Field
The utility model belongs to axial compressor, tail gas turbine field relate to rotor system, concretely relates to oval tile bearing and high-speed rotor system of four supports that tilting pad bearing formed.
Background
The axial flow compressor is widely applied to the fields of petrochemical industry, metallurgy, environmental protection, pharmacy and the like, the high-speed rotation is utilized to drive the blades to apply work to gas, the flow rate and the pressure of the gas are improved after the gas passes through the flow channel, and the tail gas turbine is commonly arranged in a unit in the petrochemical field and is used for recovering waste heat and residual pressure in the process flow. Both the axial compressor and the exhaust gas turbine belong to turbomachines and generally consist of a rotor system, a stator system and other auxiliary systems, wherein the rotor system is a core system for energy conversion, and therefore the safety and reliability of the rotor system are self-evident to the importance of the axial compressor.
The rotor dynamics is the subject of studying the dynamic characteristics of the rotor system, and particularly the core content of the dynamic problem of the high-speed rotating rotor system. Along with the development of the technological process of the related industries of turbomachinery, the requirements on chemical equipment are higher and higher, for an axial flow compressor, the pressure ratio is increased, the number of stages of the compressor is increased, equipment manufacturers have cost control requirements, the models cannot be increased, even the models are reduced by increasing the rotating speed of the compressor to meet the requirements of the technological process, the higher requirements are provided for a rotor system of the compressor, and similar problems also exist in a tail gas turbine. Meanwhile, the axial flow compressor and the tail gas turbine have the same rotating speed design requirement, so that a speed changing device can be omitted, the cost of the whole device can be greatly reduced, and the market competitiveness of the device is improved.
The number of stages of the movable blades of the compressor is increased, the span is increased, the rotating speed is increased, the critical rotating speed of the rotor is reduced, the dynamic characteristic of a rotor system cannot meet the design requirement of the dynamic standard, and the tail gas turbine also can cause the critical rotating speed problem of the rotor due to the increase of the rotating speed.
Disclosure of Invention
Not enough to prior art exists, the utility model aims to provide a high-speed rotor system of oval tile bearing and the coaxial four supports of tilting pad bearing, solve axial compressor and tail gas turbine rotor system rotordynamics design problem.
In order to solve the technical problem, the utility model discloses a following technical scheme realizes:
a four-support high-speed rotor system formed by an elliptical pad bearing and a tilting pad bearing comprises an axial flow compressor rotor and a tail gas turbine rotor which are connected through a rigid coupler;
a first elliptical tile bearing is installed on the exhaust side of the axial flow compressor rotor, and a second elliptical tile bearing is installed on the air inlet side of the axial flow compressor rotor;
a first tilting pad bearing is arranged on the exhaust side of the tail gas turbine rotor, and a second tilting pad bearing is arranged on the air inlet side of the tail gas turbine rotor;
and a shared thrust disc is arranged on the rigid coupling.
The utility model discloses still have following technical characteristic:
the diameter of the first tilting pad bearing is smaller than that of the second tilting pad bearing.
The specific pressure of the first elliptical pad bearing and the specific pressure of the second elliptical pad bearing are both between 0.8MPa and 1.5 MPa.
The specific pressure of the first tilting pad bearing and the specific pressure of the second tilting pad bearing are both between 0.5MPa and 1.0 MPa.
The axial flow compressor rotor is characterized in that a main shaft of the axial flow compressor rotor is provided with a plurality of stages of moving blades, the number of the stages is 2-20, and the length-diameter ratio of the axial flow compressor rotor is 7.5-9.
The tail gas turbine rotor is characterized in that a multi-stage moving blade is mounted at the upper cantilever end of a main shaft of the tail gas turbine rotor, the stage number is 1-3, and the length-diameter ratio of the tail gas turbine rotor is between 3.0 and 3.5.
Compared with the prior art, the utility model, following technological effect has:
and (I) the axial flow compressor rotor and the tail gas turbine rotor are directly connected through a rigid coupler to form a rotor system jointly supported by two elliptical pad bearings and two tilting pad bearings. The two rotors are mutually coupled and damped, the vibration amplitude is reduced, the amplification factor of a damping unbalance response curve corresponding to the critical rotating speed near the working rotating speed of the whole rotor system is smaller than 2.5, and the critical rotating speed is in a critical damping state, so that the dynamic design requirement of the rotor system is met.
(II) the axial flow compressor rotor and the tail gas turbine rotor are not provided with thrust discs, so that the structure is more compact and reasonable; .
(III) the axial flow compressor rotor and the tail gas turbine rotor are designed coaxially at the same rotating speed, speed change equipment is not needed, the whole unit is short in shafting, and the torsional vibration characteristic is better.
(IV) the air inlet side of the rotor of the axial flow compressor and the exhaust side of the rotor of the tail gas turbine are directly connected by a rigid coupler, a shared thrust disc is arranged on the rigid coupler, the axial forces of the two rotors are opposite, most of the axial force can be offset, the axial force of the whole rotor system is lower, and the structural arrangement is more reasonable.
Drawings
Fig. 1 is a schematic structural view of the high-speed rotor system of the present invention.
Fig. 2 is the axial force schematic diagram of the high-speed rotor system of the present invention.
The meaning of the individual reference symbols in the figures is: the method comprises the following steps of 1-axial flow compressor rotor, 2-tail gas turbine rotor, 3-rigid coupler, 4-first elliptical tile bearing, 5-second elliptical tile bearing, 6-first tilting tile bearing, 7-second tilting tile bearing and 8-shared thrust disc.
The following examples are provided to explain the present invention in further detail.
Detailed Description
The following embodiments of the present invention are given, and it should be noted that the present invention is not limited to the following embodiments, and all the equivalent transformations made on the basis of the technical solution of the present application all fall into the protection scope of the present invention.
Example 1:
the embodiment provides a four-support high-speed rotor system formed by an elliptical pad bearing and a tilting pad bearing, as shown in fig. 1 and fig. 2, the four-support high-speed rotor system comprises an axial flow compressor rotor 1 and an exhaust gas turbine rotor 2 which are connected through a rigid coupling 3;
a first elliptical tile bearing 4 is installed on the exhaust side of the axial flow compressor rotor 1, and a second elliptical tile bearing 5 is installed on the air inlet side of the axial flow compressor rotor 1;
a first tilting pad bearing 6 is arranged on the exhaust side of the tail gas turbine rotor 2, and a second tilting pad bearing 7 is arranged on the air inlet side of the tail gas turbine rotor 2;
and a shared thrust disc 8 is arranged on the rigid coupling. The shared thrust disc 8 is shared by the axial flow compressor rotor 1 and the tail gas turbine rotor 2, and the axial flow compressor rotor 1 and the tail gas turbine rotor 2 are not provided with the thrust discs respectively.
As a preferable solution of this embodiment, the diameter of the first elliptical pad bearing 4 is equal to the diameter of the second elliptical pad bearing 5; the diameter of the first tilting pad bearing 6 is smaller than the diameter of the second tilting pad bearing 7. The tail gas turbine rotor 2 is more stable in the high-speed rotation process, and the four-support high-speed rotor system is more stable in the high-speed rotation process.
As a specific solution of the present embodiment, the specific pressure of each of the first elliptical pad bearing 4 and the second elliptical pad bearing 5 is between 0.8MPa and 1.5 MPa. The specific pressure of the first tilting pad bearing 6 and the second tilting pad bearing 7 is between 0.5MPa and 1.0 MPa.
As a specific scheme of the embodiment, a main shaft of the axial flow compressor rotor 1 is provided with a plurality of stages of moving blades, the number of the stages is 12-20, and the length-diameter ratio of the axial flow compressor rotor 1 is between 7.5 and 9. A multi-stage moving blade is arranged at the upper cantilever end of a main shaft of the tail gas turbine rotor 2, the stage number is 1-3, and the length-diameter ratio of the tail gas turbine rotor 2 is between 3.0 and 3.5.
The center of gravity of the four-support high-speed rotor system of the present embodiment is between the first elliptical pad bearing 4 and the second elliptical pad bearing 5 and is close to the second elliptical pad bearing 5.
According to the technical scheme of the embodiment, the embodiment provides a specific four-support high-speed rotor system with the rotating speed of 8150 r/min.
Preferably, the span of the axial flow compressor rotor is 3100mm, 15 stages of moving blades are installed on the rotor, the diameter of a hub at the position where the impeller is installed is 400mm, the length-diameter ratio is 3100/400-7.75, the rotor is provided with two elliptical pad bearings with the bearing diameter of 125mm, the width of each bearing is 100mm, the specific pressure of a bearing at the air inlet end is 1.03MPa, and the specific pressure of a bearing at the air outlet end is 0.94 MPa.
Preferably, the span of a rotor of the tail gas turbine is 1145mm, 2 stages of moving blades are installed on the rotor, the diameter of a hub at the position where an impeller is installed is 360mm, the length-diameter ratio of the hub is 1145/360-3.18, a tilting pad bearing with the diameter of 100mm is selected at the exhaust end of the rotor, the width of the bearing is 40mm, and the specific pressure of the bearing is 0.528; the exhaust end selects a 140mm tilting pad bearing, the width of the bearing is 112mm, and the specific pressure of the bearing is 0.547.
The air inlet end of the axial flow compressor rotor is connected with the flange plate on the left side of the rigid coupling, and the flange plate on the right side of the rigid coupling is connected with the exhaust end of the tail gas turbine rotor. The rigid coupling is provided with a thrust disk in the middle, according to fig. 2 with an axial force Fa-Ft of 41.96KN, preferably with a diameter of 214mm and an axial width of 32 mm.
Claims (6)
1. The utility model provides a high-speed rotor system of four supports that oval tile bearing and tilting pad bearing formed, includes that axial compressor rotor (1) and tail gas turbine rotor (2) are connected through rigid coupling (3), its characterized in that:
a first elliptical tile bearing (4) is installed on the exhaust side of the axial flow compressor rotor (1), and a second elliptical tile bearing (5) is installed on the air inlet side of the axial flow compressor rotor (1);
a first tilting pad bearing (6) is installed on the exhaust side of the tail gas turbine rotor (2), and a second tilting pad bearing (7) is installed on the air inlet side of the tail gas turbine rotor (2);
and a shared thrust disc (8) is arranged on the rigid coupling.
2. The elliptical pad bearing and the tilting pad bearing form a four support high speed rotor system according to claim 1, characterized in that the diameter of the first tilting pad bearing (6) is smaller than the diameter of the second tilting pad bearing (7).
3. The four-support high-speed rotor system formed by the elliptical pad bearing and the tilting pad bearing according to claim 1, wherein the specific pressure of the first elliptical pad bearing (4) and the specific pressure of the second elliptical pad bearing (5) are both between 0.8MPa and 1.5 MPa.
4. The four-support high-speed rotor system formed by the elliptical pad bearing and the tilting pad bearing according to claim 1, wherein the specific pressure of the first tilting pad bearing (6) and the second tilting pad bearing (7) is between 0.5MPa and 1.0 MPa.
5. The four-support high-speed rotor system formed by the elliptical pad bearing and the tilting pad bearing as set forth in claim 1, wherein a main shaft of the axial flow compressor rotor (1) is provided with a plurality of stages of moving blades, the number of the stages is 12-20, and the length-diameter ratio of the axial flow compressor rotor (1) is 7.5-9.
6. The four-support high-speed rotor system formed by the elliptical pad bearing and the tilting pad bearing as claimed in claim 1, wherein a plurality of stages of moving blades are mounted at the cantilever end of the main shaft of the exhaust gas turbine rotor (2), the number of stages is 1-3, and the length-diameter ratio of the exhaust gas turbine rotor (2) is between 3.0 and 3.5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020428976.XU CN212428959U (en) | 2020-03-27 | 2020-03-27 | Four-support high-speed rotor system formed by elliptical pad bearing and tilting pad bearing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020428976.XU CN212428959U (en) | 2020-03-27 | 2020-03-27 | Four-support high-speed rotor system formed by elliptical pad bearing and tilting pad bearing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212428959U true CN212428959U (en) | 2021-01-29 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020428976.XU Active CN212428959U (en) | 2020-03-27 | 2020-03-27 | Four-support high-speed rotor system formed by elliptical pad bearing and tilting pad bearing |
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|---|---|
| CN (1) | CN212428959U (en) |
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2020
- 2020-03-27 CN CN202020428976.XU patent/CN212428959U/en active Active
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