CN111911538A - Bearing seat structure with cooling inner flow channel for turbo pump - Google Patents
Bearing seat structure with cooling inner flow channel for turbo pump Download PDFInfo
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- CN111911538A CN111911538A CN202010550564.8A CN202010550564A CN111911538A CN 111911538 A CN111911538 A CN 111911538A CN 202010550564 A CN202010550564 A CN 202010550564A CN 111911538 A CN111911538 A CN 111911538A
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- bearing
- bearing seat
- section
- left section
- cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C35/00—Rigid support of bearing units; Housings, e.g. caps, covers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/05—Shafts or bearings, or assemblies thereof, specially adapted for elastic fluid pumps
- F04D29/056—Bearings
- F04D29/0563—Bearings cartridges
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
- F16C37/00—Cooling of bearings
Abstract
The invention discloses a bearing seat structure with a cooling inner flow passage for a turbo pump, which comprises: the bearing seat comprises a left section of the bearing seat, a bushing and a right section of the bearing seat; the right end of the left section of the bearing seat is welded with the right section of the bearing seat through electron beam welding, the left section of the bearing seat is sleeved on the bushing, and the left section of the bearing seat is connected with the positioning step of the bushing; the right section of the bearing seat is of a rotary structure, the right section of the bearing seat and the left section of the bearing seat are welded through electron beam welding, and the right section of the bearing seat and the left section of the bearing seat are of a coaxial structure; the bush is the revolution mechanic, and the main aspects of bush are welded with the bearing frame left side section through electron beam welding, and bush and bearing frame left side section are coaxial structure, and the space between bush and the bearing frame left side section forms bearing cooling medium entry runner. The invention guarantees the pressure of the bearing cavity and the cooling flow of the bearing, and solves the problem that the turbine pump has smaller critical rotating speed margin caused by lower rigidity of the bearing seat with the cooling inner hole.
Description
Technical Field
The invention belongs to the field of turbopumps of liquid rocket engines, and particularly relates to a bearing seat structure with a cooling inner flow passage for a turbopump.
Background
The bearing seat of the turbopump of the rocket engine is arranged at the turbine end, the main function of the bearing seat is to provide support for the bearing and provide a cooling channel for the bearing, and the cooling flow comes from the centrifugal wheel and then flows to the bearing through the cooling channel arranged inside the bearing seat. The bearing block needs to provide the bearing rigidity and the enough cooling flow as much as possible for the bearing, the service life of the bearing can be shortened due to the low cooling flow, meanwhile, the pressure of a front cavity of the bearing needs to be ensured to be larger than that of the hub of the turbine disc through a flow channel of the bearing block, and otherwise, gas backflow can occur. To solve this problem, one of the common ways of designing a turbo pump is to increase the aperture of the inner flow channel, thereby reducing the flow resistance of the inner flow channel of the bearing seat, further increasing the pressure of the bearing cavity, and increasing the cooling flow of the bearing. However, the design that a part of the flow passage is positioned above the bearing can reduce the bearing support rigidity of the bearing seat, so that the critical rotating speed margin of the turbine pump is insufficient, and the risk of resonance of the turbine pump is caused.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the bearing seat structure with the cooling inner flow channel for the turbo pump is provided, and the problem that the turbine pump critical rotating speed margin is small due to the fact that the rigidity of the bearing seat with the cooling inner hole of the engine turbo pump is low is solved while the pressure of a bearing cavity and the cooling flow of a bearing are guaranteed.
The purpose of the invention is realized by the following technical scheme: a bearing housing structure with a cooling inner flow passage for a turbo pump, comprising: the bearing seat comprises a left section of the bearing seat, a bushing and a right section of the bearing seat; the right end of the left section of the bearing seat is welded with the right section of the bearing seat through electron beam welding, the left section of the bearing seat is sleeved on the bushing, and the left section of the bearing seat is connected with the positioning step of the bushing; the bearing seat right section is of a rotary structure, the bearing seat right section and the bearing seat left section are welded through electron beam welding, and the bearing seat right section and the bearing seat left section are of a coaxial structure; the bushing is of a rotary structure, the large end of the bushing is welded with the left section of the bearing seat through electron beam welding, the bushing and the left section of the bearing seat are of a coaxial structure, and a space between the bushing and the left section of the bearing seat forms a bearing cooling medium inlet flow channel; the left section of the bearing seat is provided with an inclined hole, a straight hole and a groove; wherein the bearing is disposed in the groove; the bearing cooling medium inlet flow passage is communicated with the inclined hole, the inclined hole is communicated with the straight hole, and the straight hole is communicated with the groove.
In the bearing block structure with the cooling inner flow channel for the turbo pump, the number of the inclined holes is equal to that of the straight holes, and the straight holes are parallel to the axial direction of the left section of the bearing block.
In the bearing seat structure with the cooling inner flow channel for the turbo pump, a relational formula among the number of the inclined holes, the diameter of the inclined holes and the total area of all the inclined holes is as follows:
wherein A is the total area of the inclined holes, n is the number of the inclined holes, d1The diameter of the inclined hole.
In the bearing seat structure with the cooling inner flow channel for the turbo pump, a relation formula between a required value of the bearing cooling liquid flow and the total area of all inclined holes is as follows:
wherein A is the total area of the inclined holes, m is the required value of the flow rate of the cooling liquid of the bearing, mu is the flow coefficient, P2For guiding the source pressure, P, to the bearing1The cavity pressure of the bearing cavity, ρ, cools the density of the liquid.
In the bearing block structure with the cooling inner flow channel for the turbo pump, the straight holes are uniformly distributed along the circumferential direction of the left section of the bearing block.
In the bearing seat structure with the cooling inner flow channel for the turbo pump, a relation formula between the diameter of the straight hole and the diameter of the inclined hole is as follows:
D2＝2R'
wherein d is2Is the diameter of the straight bore, R' is the radius of the bearing, D2Is the diameter of the distribution circle of the straight hole.
In the bearing seat structure with the cooling inner flow channel for the turbo pump, a deflection angle α between the axial direction of the inclined hole and the incoming flow direction is greater than 90 °.
In the bearing seat structure with the cooling inner flow channel for the turbo pump, a second positioning step with the width a of 1-2 mm is reserved at the electron beam welding part of the right section and the left section of the bearing seat.
In the bearing pedestal structure with the cooling inner flow channel for the turbo pump, the distance c between the mounting position of the left end of the bearing and the right end surface of the bushing is greater than the height of the bearing rivet in order to prevent the bearing rivet from axially colliding with the bearing pedestal.
In the bearing seat structure with the cooling inner flow channel for the turbo pump, the value of mu is 0.4-0.6; d1The value is 3 mm-5 mm.
Compared with the prior art, the invention has the following beneficial effects:
(1) according to the invention, on the premise of ensuring that the flow resistance of the bearing seat flow passage meets the cavity pressure of the bearing cavity and the cooling capacity of the bearing, the cooling flow passage of the bearing part supported by the bearing seat adopts a half-hole structure, so that the supporting rigidity of the bearing seat can be improved, the critical rotating speed of a rotor-supporting system is further improved, and the risk of rotor resonance is avoided, thereby balancing the cavity pressure of the bearing cavity, the cooling capacity of the bearing and the critical rotating speed of the rotor.
(2) The invention can lead the bearing outer ring to be in direct contact with the cooling medium, thereby achieving the purpose of cooling the bearing outer ring and the overflowing channel simultaneously, achieving better cooling effect on the bearing and improving the reliability of the bearing.
(3) The left section and the right section of the bearing seat are of split structures, so that the problem that a straight hole at the left section of the bearing seat is difficult to directly process is effectively solved, and meanwhile, the defect of strength reduction caused by welding is overcome by considering that the load of the bearing is mainly borne by the left section of the bearing seat and the load borne by an electron beam welding seam at the right side is smaller, so that the requirements of processing manufacturability and design strength of the bearing seat are met.
(4) The straight hole of the inner runner of the bearing seat is of a half-hole structure, and the inclined hole of the inner runner can be subjected to redundancy inspection and redundancy removal by using the endoscope, so that the risk of redundancy of the turbine pump is reduced, and the assembly manufacturability of the bearing seat is improved.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a front view of a bearing housing structure with a cooling inner flow passage for a turbo pump according to an embodiment of the present invention;
FIG. 2 is a sectional view taken along line A-A of FIG. 1 in accordance with an embodiment of the present invention;
FIG. 3 is a perspective view of a bearing housing structure with a cooling inner flow passage for a turbo pump according to an embodiment of the present invention;
fig. 4 is a schematic view of a working environment of a bearing seat structure provided by an embodiment of the invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a front view of a bearing housing structure with a cooling inner flow passage for a turbo pump according to an embodiment of the present invention; FIG. 2 is a sectional view taken along line A-A of FIG. 1 in accordance with an embodiment of the present invention; FIG. 3 is a perspective view of a bearing housing structure with a cooling inner flow passage for a turbo pump according to an embodiment of the present invention; fig. 4 is a schematic view of a working environment of a bearing seat structure provided by an embodiment of the invention.
As shown in fig. 1 to 4, the bearing housing structure with a cooling inner flow passage for a turbo pump includes: the bearing seat comprises a bearing seat left section 1, a bushing 2 and a bearing seat right section 3; wherein the content of the first and second substances,
the right end of the bearing seat left section 1 is welded with the bearing seat right section 3 through electron beam welding, the bearing seat left section 1 is sleeved on the bushing 2, and the bearing seat left section 1 is connected with the positioning step 21 of the bushing 2; the bearing seat right section 3 is of a rotary structure, the bearing seat right section 3 and the bearing seat left section 1 are welded through electron beam welding, and the bearing seat right section 3 and the bearing seat left section 1 are of a coaxial structure; the bushing 2 is of a rotary structure, the large end of the bushing 2 is welded with the left section 1 of the bearing seat through electron beam welding, the bushing 2 and the left section 1 of the bearing seat are of a coaxial structure, and a space between the bushing 2 and the left section 1 of the bearing seat forms a bearing cooling medium inlet flow passage 22; the left section 1 of the bearing seat is provided with an inclined hole 11, a straight hole 12 and a groove 13; wherein the bearing 6 is arranged in the groove 13; the bearing cooling medium inlet flow passage 22 is communicated with the inclined hole 11, the inclined hole 11 is communicated with the straight hole 12, and the straight hole 12 is communicated with the groove 13.
In the above embodiment, the number of the inclined holes 11 and the number of the straight holes 12 are equal, and the straight holes 12 are parallel to the axial direction of the bearing seat left section 1. A plurality of straight holes 12 are uniformly distributed along the circumferential direction of the bearing seat left section 1. A plurality of straight holes 12 form a circle.
The method for determining the inner aperture and the number of the left section 1 of the bearing seat comprises the following steps: and determining the cavity pressure of a bearing cavity according to the pressure of a cooling bearing drainage source and the pressure at the hub of the turbine disc and the minimum pressure difference for preventing gas from flowing backwards, and preliminarily determining the number of the inclined holes 11 in the left section 1 of the bearing seat by combining the required value of the cooling flow of the bearing. The constraint relation among the total area of the inclined holes 11, the number of the inclined holes 11, the cooling flow, the pressure and other parameters is as follows:
wherein A is the total area of the inclined holes 11, m is the required value of the cooling flow of the bearing, mu is the flow coefficient, and the value is 0.4-0.6, P2For guiding the source pressure, P, to the bearing1For the cavity pressure of the bearing cavity, n is the number of the inclined holes 11, d1The diameter of the inclined hole 11 is 3 mm-5 mm.
The number of the inclined holes 11 is preliminarily determined according to the above relation. The number of the straight holes 12 is equal to the number of the inclined holes 11, the diameters of the straight holes 12 and the inclined holes 11, and the constraint relation between the diameter of the distribution circle of the straight holes 12 and the outer radius of the bearing installed on the bearing seat are as follows:
D2＝2R'
wherein d is2Is the diameter of the straight bore 12, R' is the radius of the bearing, D2The diameter of the circumference formed by the plurality of straight holes 12. In the first relational expression of the above formula, the left formula only needs to be slightly larger than the right formula.
Based on the preliminary structure, the flow resistance and the rigidity of the bearing seat are calculated through accurate simulation, and the inner aperture and the number of the left section 1 of the bearing seat are adjusted according to the requirements of the flow resistance and the rigidity of the bearing seat.
Referring to fig. 1 to 4, a bearing seat structure with a cooling inner flow channel for a turbo pump comprises a bearing seat left section, a bushing and a bearing seat right section, which are connected into a whole in an electron beam welding mode. In fig. 4, reference numeral 4 is a rotation shaft; reference numeral 5 is a turbine housing; reference numeral 6 is a bearing; reference numeral 7 is a shaft sleeve; reference numeral 8 denotes a bearing cooling flow path.
And the cooling channel in the left section structure of the bearing seat is formed by an inclined hole and a straight hole. The straight hole supporting the bearing part adopts a half-hole structure to improve the bearing support rigidity of the bearing seat, so that the aim of improving the critical rotating speed of the turbine pump is fulfilled, for the applied example, after the half-hole structure is adopted, under the condition that the flow area is increased by 17.7%, the bearing rigidity is improved by 6.2%, and meanwhile, the functions of reducing the flow resistance of a flow passage in the bearing seat and improving the rigidity of the bearing seat are realized. The right end of the left section of the bearing seat is welded with the right section of the bearing seat through electron beam welding, and the middle of the left section of the bearing seat is welded with the lining through electron beam welding. The left section of the bearing seat comprises a plurality of inclined holes and straight holes along the axial direction, the left ends of the inclined holes are communicated with an annular inlet flow passage formed by the lining and the left section of the bearing seat, the right ends of the inclined holes are communicated with the straight holes, the number of the inclined holes is equal to that of the straight holes, and every two of the inclined holes and the straight holes are communicated in an intersecting manner.
The bearing seat right section is of a rotary structure and is welded with the bearing seat left section through electron beam welding, and the bearing seat right section and the bearing seat left section are of a coaxial structure.
The bushing is of a rotary structure, the large end of the bushing is welded with the left section of the bearing seat through electron beam welding, the bushing and the left section of the bearing seat are of a coaxial structure, and the bushing and the left section of the bearing seat form an annular inlet flow channel for a bearing cooling medium.
In order to reduce the bending flow resistance, the deflection angle alpha between the inclined hole in the left section of the bearing seat and the incoming flow direction is larger than 90 degrees.
And a positioning step with the width a of 1-2 mm is reserved at the electron beam welding part of the right section and the left section of the bearing seat.
Carry out electron beam welding with bearing frame left side section and bearing frame right side section, then carry out the finish machining to the internal surface, bearing frame left side section and bearing left end face cooperation department radius to reduce stress concentration, the radius of fillet should be less than the radius of fillet of bearing, general radius R is taken to be 0.5 mm-1 mm.
In order to reduce the structural weight and consider the feasibility of the inspection of the redundancy of the turbine pump, after the left section and the right section of the bearing seat are welded, a proper amount of lightening holes are processed at the big end and are uniformly distributed along the circumferential direction.
And processing the welding part of the left section of the bearing seat and the bush, wherein a positioning step is reserved at the bottom of the electron beam welding of the left section of the bearing seat and the bush, the step plays a role of preventing welding spatter, and the step height b is 1-2 mm.
And (4) checking and removing scrap iron and other redundancies in the straight hole and the inclined hole of the left section of the bearing seat, and cleaning and drying the scrap iron and other redundancies.
And (3) carrying out electron beam welding on the left section of the bearing seat and the bush, and processing the welded right end surface and the inner surface of the bush after welding, wherein the distance c between the left end mounting position of the bearing and the right end surface of the bush is greater than the height of the bearing rivet after processing for preventing the bearing rivet from axially colliding and rubbing with the bearing seat.
According to the invention, on the premise of ensuring that the flow resistance of the bearing seat flow passage meets the cavity pressure of the bearing cavity and the cooling capacity of the bearing, the cooling flow passage of the bearing part supported by the bearing seat adopts a half-hole structure, so that the supporting rigidity of the bearing seat can be improved, the critical rotating speed of a rotor-supporting system is further improved, and the risk of rotor resonance is avoided, thereby balancing the cavity pressure of the bearing cavity, the cooling capacity of the bearing and the critical rotating speed of the rotor.
The invention can lead the bearing outer ring to be in direct contact with the cooling medium, thereby achieving the purpose of cooling the bearing outer ring and the overflowing channel simultaneously, achieving better cooling effect on the bearing and improving the reliability of the bearing.
The left section and the right section of the bearing seat are of split structures, so that the problem that a straight hole at the left section of the bearing seat is difficult to directly process is effectively solved, and meanwhile, the defect of strength reduction caused by welding is overcome by considering that the load of the bearing is mainly borne by the left section of the bearing seat and the load borne by an electron beam welding seam at the right side is smaller, so that the requirements of processing manufacturability and design strength of the bearing seat are met.
The straight hole of the inner runner of the bearing seat is of a half-hole structure, and the inclined hole of the inner runner can be subjected to redundancy inspection and redundancy removal by using the endoscope, so that the risk of redundancy of the turbine pump is reduced, and the assembly manufacturability of the bearing seat is improved.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. The utility model provides a bearing frame structure of runner in area cooling for turbo pump which characterized in that includes: the bearing seat comprises a bearing seat left section (1), a bushing (2) and a bearing seat right section (3); wherein the content of the first and second substances,
the right end of the bearing seat left section (1) is welded with the bearing seat right section (3) through electron beam welding, the bearing seat left section (1) is sleeved on the bushing (2), and the bearing seat left section (1) is connected with a positioning step (21) of the bushing (2);
the bearing seat right section (3) is of a rotary structure, the bearing seat right section (3) and the bearing seat left section (1) are welded through electron beam welding, and the bearing seat right section (3) and the bearing seat left section (1) are of a coaxial structure;
the bushing (2) is of a rotary structure, the large end of the bushing (2) is welded with the left section (1) of the bearing seat through electron beam welding, the bushing (2) and the left section (1) of the bearing seat are of a coaxial structure, and a space between the bushing (2) and the left section (1) of the bearing seat forms a bearing cooling medium inlet flow channel (22);
the left section (1) of the bearing seat is provided with an inclined hole (11), a straight hole (12) and a groove (13); wherein the bearing (6) is arranged in the groove (13); the bearing cooling medium inlet flow passage (22) is communicated with the inclined hole (11), the inclined hole (11) is communicated with the straight hole (12), and the straight hole (12) is communicated with the groove (13).
2. The bearing housing structure with a cooling inner flow passage for a turbo pump according to claim 1, wherein: the number of the inclined holes (11) is equal to that of the straight holes (12), and the straight holes (12) are parallel to the axial direction of the left section (1) of the bearing seat.
3. The bearing housing structure with a cooling inner flow passage for a turbo pump according to claim 1, wherein: the relation formula among the number of the inclined holes (11), the diameter of the inclined holes (11) and the total area of all the inclined holes (11) is as follows:
wherein A is the total area of the inclined holes (11), n is the number of the inclined holes (11), d1Is the diameter of the inclined hole (11).
4. A bearing housing structure with a cooling inner flow passage for a turbo pump according to claim 3, wherein: the relation formula between the required value of the bearing cooling liquid flow and the total area of all the inclined holes (11) is as follows:
wherein A is the total area of the inclined holes (11), m is the required value of the flow rate of the bearing cooling liquid, mu is the flow coefficient, P2For guiding the source pressure, P, to the bearing1The cavity pressure of the bearing cavity, ρ, cools the density of the liquid.
5. A bearing housing structure with a cooling inner flow passage for a turbo pump according to claim 3, wherein: the straight holes (12) are uniformly distributed along the circumferential direction of the left section (1) of the bearing seat.
6. The bearing housing structure with a cooling inner flow passage for a turbo pump according to claim 5, wherein: the relation formula of the diameter of the straight hole (12) and the diameter of the inclined hole (11) is as follows:
D2＝2R'
wherein d is2Is the diameter of the straight hole (12), R' is the radius of the bearing, D2Is the diameter of the distribution circle of the straight holes (12).
7. The bearing housing structure with a cooling inner flow passage for a turbo pump according to claim 1, wherein: the deflection angle alpha between the axial direction of the inclined hole (11) and the incoming flow direction is larger than 90 degrees.
8. The bearing housing structure with a cooling inner flow passage for a turbo pump according to claim 1, wherein: and a second positioning step with the width a of 1-2 mm is reserved at the electron beam welding part of the right section (3) and the left section (1) of the bearing seat.
9. The bearing housing structure with a cooling inner flow passage for a turbo pump according to claim 1, wherein: in order to prevent the bearing rivet from axially colliding and rubbing with the bearing seat, the distance c between the mounting position of the left end of the bearing and the right end face of the bushing (2) is greater than the height of the bearing rivet.
10. The bearing housing structure with a cooling inner flow passage for a turbo pump according to claim 5, wherein: mu is 0.4-0.6; d1The value is 3 mm-5 mm.
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|---|---|---|---|
| CN202010550564.8A CN111911538B (en) | 2020-06-16 | 2020-06-16 | Bearing seat structure with cooling inner flow channel for turbo pump |
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| CN202010550564.8A CN111911538B (en) | 2020-06-16 | 2020-06-16 | Bearing seat structure with cooling inner flow channel for turbo pump |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112648027A (en) * | 2020-12-09 | 2021-04-13 | 西安航天动力研究所 | Positioning structure for improving critical rotating speed of turbine rotor |
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| CN111911538B (en) | 2022-03-04 |
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