CN216483954U - Connecting structure for full-speed dynamic balance experiment of heavy gas turbine - Google Patents
Connecting structure for full-speed dynamic balance experiment of heavy gas turbine Download PDFInfo
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- CN216483954U CN216483954U CN202123096130.4U CN202123096130U CN216483954U CN 216483954 U CN216483954 U CN 216483954U CN 202123096130 U CN202123096130 U CN 202123096130U CN 216483954 U CN216483954 U CN 216483954U
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Abstract
A connecting structure for a full-speed dynamic balance experiment of a heavy-duty gas turbine comprises a full-speed dynamic balance process shaft sleeve, a full-speed dynamic balancer universal coupling, a gas turbine rotor front shaft neck and a full-speed dynamic balancer bearing bush; an outer flange is arranged at the front end cylinder opening of the shaft sleeve in the full-speed dynamic balance process, an inner flange is arranged at the rear end cylinder opening, and a rotor switching section is arranged between the inner flange and the rear end cylinder opening; the full-speed dynamic balancing process shaft sleeve is fixedly connected with a full-speed dynamic balancing machine universal coupling through an outer flange and a bolt; the full-speed dynamic balance process shaft sleeve is in interference insertion fit with the front shaft neck of the gas turbine rotor through the rotor switching section, and the full-speed dynamic balance process shaft sleeve is fixedly connected with the front shaft neck of the gas turbine rotor through an inner flange and a bolt; the outer circle diameter of the full-speed dynamic balancing process shaft sleeve is matched with the inner circle diameter of a full-speed dynamic balancing machine bearing bush, and the full-speed dynamic balancing process shaft sleeve is matched with a full-speed dynamic balancing machine bearing bush support; the form and position tolerance and the roughness of the excircle surface of the full-speed dynamic balance process shaft sleeve are the same as those of the excircle reference surface of the front fulcrum of the gas turbine rotor.
Description
Technical Field
The utility model belongs to the technical field of heavy gas turbine dynamic balance experiment, especially, relate to a connection structure that is used for heavy gas turbine full speed dynamic balance experiment.
Background
The front supporting point of a rotor of a certain heavy-duty gas turbine is internally suspended and is wrapped by a 1-3 level drum barrel of an air compressor, so that the front supporting point of the rotor of the heavy-duty gas turbine cannot be supported and matched with a bearing bush of a full-speed dynamic balancing machine, the full-speed dynamic balancing experiment of the heavy-duty gas turbine is never realized, and the slow-speed dynamic balancing experiment can only be carried out on the heavy-duty gas turbine in the past. Since the heavy-duty gas turbine has never been subjected to full-speed dynamic balance experiments before, the vibration value of the gas turbine rotor is often too large during the test of a power plant, and even a shutdown condition is caused. Therefore, full-speed dynamic balance experiments for heavy-duty gas turbines are imperative.
SUMMERY OF THE UTILITY MODEL
The problem that exists to prior art, the utility model provides a connection structure for heavy gas turbine full speed dynamic balance experiment has realized heavy gas turbine's full speed dynamic balance experiment for the first time, through full speed dynamic balance experiment back, when the power plant is tested a car, the vibration value of gas turbine rotor reduces by a wide margin, has established the basis for heavy gas turbine's operational reliability.
In order to achieve the above purpose, the utility model adopts the following technical scheme: a connecting structure for full-speed dynamic balance experiments of a heavy-duty gas turbine comprises a full-speed dynamic balance process shaft sleeve, a full-speed dynamic balancer universal coupling, a gas turbine rotor front journal and a full-speed dynamic balancer bearing bush; an outer flange is arranged at a front end cylinder opening of the full-speed dynamic balance process shaft sleeve, an inner flange is arranged at a rear end cylinder opening of the full-speed dynamic balance process shaft sleeve, and a part between the inner flange and the rear end cylinder opening of the full-speed dynamic balance process shaft sleeve is used as a rotor switching section; the full-speed dynamic balancing process shaft sleeve is fixedly connected with a full-speed dynamic balancing machine universal coupling through an outer flange and a bolt; the full-speed dynamic balance process shaft sleeve is in interference insertion fit with the front shaft neck of the gas turbine rotor through the rotor switching section, and is fixedly connected with the front shaft neck of the gas turbine rotor through an inner flange and a bolt; the outer circle diameter of the full-speed dynamic balancing process shaft sleeve is matched with the inner circle diameter of the full-speed dynamic balancing machine bearing bush, and the full-speed dynamic balancing process shaft sleeve is matched with the full-speed dynamic balancing machine bearing bush support.
The form and position tolerance and the roughness of the excircle surface of the shaft sleeve in the full-speed dynamic balance process are the same as those of the excircle reference surface of the front supporting point of the rotor of the gas turbine.
The utility model has the advantages that:
the utility model discloses a connection structure for heavy gas turbine full speed dynamic balance experiment has realized heavy gas turbine's full speed dynamic balance experiment for the first time, through full speed dynamic balance experiment back, and when the power plant was tested a car, the vibration value of gas turbine rotor reduced by a wide margin, has established the basis for heavy gas turbine's operational reliability.
Drawings
FIG. 1 is a schematic diagram of a connection structure for a full speed dynamic balance test of a heavy duty gas turbine according to the present invention;
in the figure, 1 is a full-speed dynamic balancing process shaft sleeve, 2 is a full-speed dynamic balancing machine universal coupling, 3 is a gas turbine rotor front journal, 4 is a full-speed dynamic balancing machine bearing bush, 5 is a gas turbine rotor front fulcrum, 6 is a compressor drum barrel, 11 is an outer flange, 12 is an inner flange, and 13 is a rotor adapter section.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
As shown in fig. 1, a connecting structure for a full-speed dynamic balance experiment of a heavy-duty gas turbine comprises a full-speed dynamic balance process shaft sleeve 1, a full-speed dynamic balancer universal coupling 2, a gas turbine rotor front journal 3 and a full-speed dynamic balancer bearing bush 4; an outer flange 11 is arranged at the front end cylindrical opening of the full-speed dynamic balance process shaft sleeve 1, an inner flange 12 is arranged at the rear end cylindrical opening of the full-speed dynamic balance process shaft sleeve 1, and the part between the inner flange 12 and the rear end cylindrical opening of the full-speed dynamic balance process shaft sleeve 1 is used as a rotor switching section 13; the full-speed dynamic balancing process shaft sleeve 1 is fixedly connected with a full-speed dynamic balancing machine universal coupling 2 through an outer flange 11 and a bolt; the full-speed dynamic balance process shaft sleeve 1 is in interference insertion fit with the front shaft neck 3 of the gas turbine rotor through the rotor switching section 13, and the full-speed dynamic balance process shaft sleeve 1 is fixedly connected with the front shaft neck 3 of the gas turbine rotor through the inner flange 12 and the bolts; the outer circle diameter of the full-speed dynamic balancing process shaft sleeve 1 is matched with the inner circle diameter of the full-speed dynamic balancing machine bearing bush 4, so that the design and manufacturing cost of the full-speed dynamic balancing machine bearing bush 4 can be saved, the construction period can be shortened, and the full-speed dynamic balancing process shaft sleeve 1 is in supporting fit with the full-speed dynamic balancing machine bearing bush 4.
The form and position tolerance and the roughness of the excircle surface of the full-speed dynamic balance process shaft sleeve 1 are the same as those of the excircle reference surface of the front fulcrum 5 of the gas turbine rotor. Specifically, the outer circular surface of the full-speed dynamic balance process shaft sleeve 1 and the outer circular reference surface of the front supporting point 5 of the gas turbine rotor can obtain the same surface process parameters by adopting a one-time clamping processing mode so as to ensure that the full-speed dynamic balance state and the working state of the heavy gas turbine rotor are kept consistent.
Before the full-speed dynamic balance process shaft sleeve 1 is connected with the front shaft neck 3 of the gas turbine rotor, the full-speed dynamic balance process shaft sleeve 1 is heated to a specified temperature, then the heated full-speed dynamic balance process shaft sleeve 1 rotor switching section 13 is hot-mounted on the front shaft neck 3 of the gas turbine rotor, until the temperature is reduced to normal temperature, the full-speed dynamic balance process shaft sleeve 1 and the front shaft neck 3 of the gas turbine rotor are in interference connection, and then the inner flange 12 and the front shaft neck 3 of the gas turbine rotor are fixedly connected together by eight M16 high-strength bolts, so that the transmission requirement of torque is guaranteed.
After the full-speed dynamic balance process shaft sleeve 1 and the front journal 3 of the gas turbine rotor are assembled, the full-speed dynamic balance process shaft sleeve 1 is connected with a full-speed dynamic balance machine universal coupling 2, and then a full-speed dynamic balance machine bearing bush 4 is supported and matched on the outer circular surface of the full-speed dynamic balance process shaft sleeve 1, namely, a front pivot 5 of the gas turbine rotor suspended in the full-speed dynamic balance process shaft sleeve 1 is moved forwards. And starting the full-speed dynamic balancing machine, so that a full-speed dynamic balancing experiment can be carried out.
The embodiments are not intended to limit the scope of the present invention, and all equivalent implementations or modifications that do not depart from the scope of the present invention are intended to be included within the scope of the present invention.
Claims (2)
1. A connection structure for full-speed dynamic balance experiment of a heavy-duty gas turbine is characterized in that: the full-speed dynamic balancing machine comprises a full-speed dynamic balancing process shaft sleeve, a full-speed dynamic balancing machine universal coupling, a gas turbine rotor front journal and a full-speed dynamic balancing machine bearing bush; an outer flange is arranged at a front end cylinder opening of the full-speed dynamic balance process shaft sleeve, an inner flange is arranged at a rear end cylinder opening of the full-speed dynamic balance process shaft sleeve, and a part between the inner flange and the rear end cylinder opening of the full-speed dynamic balance process shaft sleeve is used as a rotor switching section; the full-speed dynamic balancing process shaft sleeve is fixedly connected with a full-speed dynamic balancing machine universal coupling through an outer flange and a bolt; the full-speed dynamic balance process shaft sleeve is in interference insertion fit with the front shaft neck of the gas turbine rotor through the rotor switching section, and is fixedly connected with the front shaft neck of the gas turbine rotor through an inner flange and a bolt; the outer circle diameter of the full-speed dynamic balancing process shaft sleeve is matched with the inner circle diameter of the full-speed dynamic balancing machine bearing bush, and the full-speed dynamic balancing process shaft sleeve is matched with the full-speed dynamic balancing machine bearing bush support.
2. The connecting structure for the full-speed dynamic balance experiment of the heavy-duty gas turbine as claimed in claim 1, wherein: the form and position tolerance and the roughness of the excircle surface of the shaft sleeve in the full-speed dynamic balance process are the same as those of the excircle reference surface of the front supporting point of the rotor of the gas turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123096130.4U CN216483954U (en) | 2021-12-10 | 2021-12-10 | Connecting structure for full-speed dynamic balance experiment of heavy gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123096130.4U CN216483954U (en) | 2021-12-10 | 2021-12-10 | Connecting structure for full-speed dynamic balance experiment of heavy gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216483954U true CN216483954U (en) | 2022-05-10 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123096130.4U Active CN216483954U (en) | 2021-12-10 | 2021-12-10 | Connecting structure for full-speed dynamic balance experiment of heavy gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216483954U (en) |
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2021
- 2021-12-10 CN CN202123096130.4U patent/CN216483954U/en active Active
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