CN114278606A - Multi-working-medium helium gas compressor main shaft structure - Google Patents
Multi-working-medium helium gas compressor main shaft structure Download PDFInfo
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- CN114278606A CN114278606A CN202111627359.8A CN202111627359A CN114278606A CN 114278606 A CN114278606 A CN 114278606A CN 202111627359 A CN202111627359 A CN 202111627359A CN 114278606 A CN114278606 A CN 114278606A
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Abstract
The invention discloses a multi-working-medium helium gas compressor main shaft structure which comprises a gas compressor shaft, a turbine shaft and a core shaft, wherein a first groove is formed in the rear end face of the gas compressor shaft, the front end of the turbine shaft is embedded into the first groove, a core shaft hole is formed in the center of the gas compressor shaft, a second groove is formed in the front end face of the turbine shaft, the rear end of the core shaft is embedded into the second groove, and the front end of the core shaft penetrates out of the core shaft hole. The invention can effectively reduce the value of the critical rotating speed of the helium compressor rotor, and greatly reduce the energy value of response when crossing the critical rotating speed; through the connecting structure of the sectional shaft and the flexible sleeve gear, the tolerance of machining errors and assembly accumulated errors of the stator parts is widened.
Description
Technical Field
The invention belongs to the technical field of hypersonic air suction type combined engines, and relates to a multi-working-medium helium gas compressor main shaft structure based on flexible sleeve gear connection, which is suitable for a long-span, multi-fulcrum and high-pressure-ratio high-speed rotating mechanism.
Background
In the field of hypersonic air-breathing combined engines, the method of widening the working envelope of a turbine engine by using more efficient thermodynamic cycle is the most effective means adopted in the field of combined engines at present. In the efficient thermodynamic cycle process, a high-performance pressurization link is an important component in a closed cycle system.
According to the specific requirements of thermodynamic cycle, helium with various working media, namely high-heat-melting-ratio helium is selected as a closed cycle working medium in the pressurization link, and high-temperature fuel gas is used as a power source of the high-speed rotating mechanism. Based on the requirement of high pressure ratio and the characteristic that helium is difficult to compress, the rotary mechanism has the characteristics of multiple pivots, long span and high rotation speed.
Disclosure of Invention
Objects of the invention
The purpose of the invention is: the multi-working-medium helium compressor main shaft structure can meet the normal operation of a helium compressor with multiple supporting points, long span and high rotating speed.
(II) technical scheme
In order to solve the technical problem, the invention provides a multi-working-medium helium gas compressor main shaft structure which comprises a gas compressor shaft, a turbine shaft and a core shaft, wherein a first groove is formed in the rear end face of the gas compressor shaft, the front end of the turbine shaft is embedded into the first groove, a core shaft hole is formed in the center of the gas compressor shaft, a second groove is formed in the front end face of the turbine shaft, the rear end of the core shaft is embedded into the second groove, and the front end of the core shaft penetrates out of the core shaft hole.
The outer peripheral surface of the front end of the turbine shaft is provided with a flexible gear sleeve, and the turbine shaft is in torque transmission with the compressor shaft through an internal spline.
The outer peripheral surface of the front end of the turbine shaft is provided with a cylindrical surface, the cylindrical surface is positioned at the rear part of the flexible gear sleeve, the cylindrical surface and the compressor shaft are centered, and the mandrel and the compressor shaft are tensioned to carry out axial positioning.
Wherein, on the compressor shaft, the span of the front middle fulcrum is 500 mm.
And the span of the middle and rear supporting points on the compressor shaft and the turbine shaft is 300 mm.
Wherein, on the compressor shaft, the front support point rigidity is 5E + 06N/m.
Wherein, on the compressor shaft, the rigidity of the middle pivot point is 8E + 07N/m.
Wherein, on the turbine shaft, the rear fulcrum rigidity is 5E + 06N/m.
On the turbine shaft, the number of the internal spline teeth is 28, the modulus of the internal spline is 1, and the pressure angle of the internal spline is 30 degrees.
And the matching tolerance of the positioning surface between the compressor shaft and the turbine shaft is H7/g 6.
(III) advantageous effects
The multi-working-medium helium gas compressor main shaft structure provided by the technical scheme can effectively reduce the value of the critical rotating speed of the helium gas compressor rotor, and greatly reduce the energy value of response when the critical rotating speed is crossed; through the connecting structure of the sectional shaft and the flexible sleeve gear, the tolerance of machining errors and assembly accumulated errors of the stator parts is widened.
Drawings
FIG. 1 shows a flexible sleeve tooth joint structure at the middle of a shaft;
fig. 2 shows the pivot position and the whole axis structure.
Detailed Description
In order to make the objects, contents and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.
The multi-working-medium helium compressor needs to span multi-stage critical rotating speed when reaching a working rotating speed interval, comprises oscillating heads, translation equal vibration modes and has extremely high requirements on the processing precision and the assembling precision of parts.
Referring to fig. 1 and 2, the multi-working-medium helium compressor main shaft structure in the embodiment includes a compressor shaft, a turbine shaft and a mandrel, a first groove is formed in a rear end face of the compressor shaft, a front end of the turbine shaft is embedded into the first groove, a mandrel hole is formed in the center of the compressor shaft, a second groove is formed in a front end face of the turbine shaft, a rear end of the mandrel is embedded into the second groove, and the front end of the mandrel penetrates out of the mandrel hole.
The peripheral surface of the front end of the turbine shaft is provided with a flexible gear sleeve, and the turbine shaft is in torque transmission with the compressor shaft through an internal spline. The outer peripheral surface of the front end of the turbine shaft is provided with a cylindrical surface, the cylindrical surface is positioned at the rear part of the flexible gear sleeve, the cylindrical surface and the compressor shaft are centered, and the mandrel and the compressor shaft are tensioned to carry out axial positioning.
On the basis of meeting the overall structural requirements of the gas compressor, the critical rotating speed values of all orders under the working rotating speed interval are reduced and the tolerance of part machining errors and assembly errors is improved by selecting appropriate structural parameters including the positions and spans of the front fulcrum, the middle fulcrum and the rear fulcrum, the supporting rigidity of all the fulcrums and the flexible sleeve gear parameters.
The key parameters in the structure mainly comprise fulcrum span, support rigidity, main shaft section position and flexible sleeve tooth parameters. The fulcrum span and the supporting rigidity range of each fulcrum are preliminarily selected according to the overall requirements, after several rounds of rotor dynamics simulation calculation iteration are carried out, the main shaft sectional position and the flexible sleeve tooth parameters (including internal spline parameters, the axial length of a positioning surface and the shaft hole matching tolerance) are selected, and the target critical rotating speed interval has enough safety margin compared with the working rotating speed interval and is generally considered according to +/-2000 rpm.
Several key parameters in the structure are selected from the following table
| Front mid-pivot span | Mid-to-rear branch span | Front pivot stiffness | Mid pivot point stiffness | Stiffness of rear pivot |
| 500mm | 300mm | 5E+06N/m | 8E+07N/m | 5E+06N/m |
| Number of internal spline teeth | Modulus of internal spline | Internal spline pressure angle | Tolerance of fit of locating surfaces | |
| 28 | 1 | 30° | H7/g6 |
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A multi-working-medium helium gas compressor main shaft structure is characterized by comprising a gas compressor shaft, a turbine shaft and a core shaft, wherein a first groove is formed in the rear end face of the gas compressor shaft, the front end of the turbine shaft is embedded into the first groove, a core shaft hole is formed in the center of the gas compressor shaft, a second groove is formed in the front end face of the turbine shaft, the rear end of the core shaft is embedded into the second groove, and the front end of the core shaft penetrates out of the core shaft hole.
2. The multi-working-medium helium gas compressor main shaft structure of claim 1, wherein a flexible gear sleeve is arranged on the outer peripheral surface of the front end of the turbine shaft, and the turbine shaft is in torque transmission with the compressor shaft through an internal spline.
3. The multi-working-medium helium gas compressor spindle structure of claim 2, wherein the outer peripheral surface of the front end of the turbine shaft is provided with a cylindrical surface, the cylindrical surface is positioned at the rear part of the flexible gear sleeve, and is centered with the compressor shaft through the cylindrical surface, and is tensioned with the compressor shaft through the mandrel for axial positioning.
4. The multi-working substance helium compressor spindle configuration of claim 3, wherein the compressor shaft has a front-to-mid fulcrum span of 500 mm.
5. The multi-working-medium helium compressor spindle configuration of claim 4, wherein the compressor shaft and turbine shaft have a mid-to-aft point span of 300 mm.
6. The multi-working mass helium compressor spindle configuration of claim 5, wherein the compressor shaft has a forward pivot stiffness of 5E + 06N/m.
7. The multi-working substance helium compressor spindle configuration of claim 6, wherein the mid-pivot stiffness on the compressor shaft is 8E + 07N/m.
8. The multi-working-medium helium compressor spindle structure of claim 7, wherein the aft-fulcrum stiffness on the turbine shaft is 5E + 06N/m.
9. The multi-working-medium helium compressor main shaft structure of claim 8, wherein on the turbine shaft, the number of the internal splines is 28, the module of the internal splines is 1, and the pressure angle of the internal splines is 30 °.
10. The multi-working substance helium compressor spindle configuration of claim 9, wherein the seating surface between the compressor shaft and the turbine shaft has a fit tolerance of H7/g 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111627359.8A CN114278606A (en) | 2021-12-28 | 2021-12-28 | Multi-working-medium helium gas compressor main shaft structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111627359.8A CN114278606A (en) | 2021-12-28 | 2021-12-28 | Multi-working-medium helium gas compressor main shaft structure |
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| Publication Number | Publication Date |
|---|---|
| CN114278606A true CN114278606A (en) | 2022-04-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111627359.8A Pending CN114278606A (en) | 2021-12-28 | 2021-12-28 | Multi-working-medium helium gas compressor main shaft structure |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070212226A1 (en) * | 2006-01-27 | 2007-09-13 | Snecma | radially-compact assembly between a turbine shaft and a stub axle of a turbomachine compressor shaft |
| CN102927141A (en) * | 2012-10-24 | 2013-02-13 | 哈尔滨东安发动机（集团）有限公司 | Coupler assembly |
| CN102975387A (en) * | 2012-12-06 | 2013-03-20 | 江苏省徐州锻压机床厂集团有限公司 | Servo motor connecting mode |
| CN105757130A (en) * | 2016-04-19 | 2016-07-13 | 哈尔滨东安发动机（集团）有限公司 | Engine turbine and compressor rotor connection and torque transmission device |
| CN109968012A (en) * | 2019-04-16 | 2019-07-05 | 西安航天动力研究所 | A kind of tightening method and axially loaded formula screwing tool of helium turbine shafting |
| CN113530878A (en) * | 2021-08-03 | 2021-10-22 | 中车大连机车研究所有限公司 | Main shaft connecting structure of turbocharger |
-
2021
- 2021-12-28 CN CN202111627359.8A patent/CN114278606A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070212226A1 (en) * | 2006-01-27 | 2007-09-13 | Snecma | radially-compact assembly between a turbine shaft and a stub axle of a turbomachine compressor shaft |
| CN102927141A (en) * | 2012-10-24 | 2013-02-13 | 哈尔滨东安发动机（集团）有限公司 | Coupler assembly |
| CN102975387A (en) * | 2012-12-06 | 2013-03-20 | 江苏省徐州锻压机床厂集团有限公司 | Servo motor connecting mode |
| CN105757130A (en) * | 2016-04-19 | 2016-07-13 | 哈尔滨东安发动机（集团）有限公司 | Engine turbine and compressor rotor connection and torque transmission device |
| CN109968012A (en) * | 2019-04-16 | 2019-07-05 | 西安航天动力研究所 | A kind of tightening method and axially loaded formula screwing tool of helium turbine shafting |
| CN113530878A (en) * | 2021-08-03 | 2021-10-22 | 中车大连机车研究所有限公司 | Main shaft connecting structure of turbocharger |
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