CN114683006A

CN114683006A - Novel air-floatation thrust bearing and manufacturing method thereof

Info

Publication number: CN114683006A
Application number: CN202210427991.6A
Authority: CN
Inventors: 邓成林; 叶凌; 吴淑霞; 李成铭; 石燕青
Original assignee: Tianjin Jieqiang Power Equipment Co ltd
Current assignee: Tianjin Jieqiang Power Equipment Co ltd
Priority date: 2022-04-22
Filing date: 2022-04-22
Publication date: 2022-07-01

Abstract

The invention discloses a novel air-float thrust bearing and a manufacturing method thereof, comprising the following steps: the middle part of the thrust frame is provided with a thrust disc; the two ends of the rotor are sleeved with radial bearings, and one end of the rotor penetrates out and is connected with the thrust disc; cooling foils detachably arranged on two sides of the thrust disc; the air floatation foil is detachably arranged in the two radial bearing inner rings; the invention designs the air floatation foil which can be sleeved on two ends of a high-speed rotating rotor and is sleeved on the inner ring in the radial direction, the rigid air film on the outer side of the rotor can be effectively manufactured, air floatation is realized, friction is reduced, the rotating speed of the rotor is improved, and the cooling foil on two sides of the thrust disk which can be connected with the front end of the rotor can be used for effectively cooling the thrust disk rotating at high speed, so that the structure is more stable and durable.

Description

Novel air-floatation thrust bearing and manufacturing method thereof

Technical Field

The invention relates to the field of devices related to culture fans, in particular to a novel air-floatation thrust bearing and a manufacturing method thereof.

Background

The cultivation fan is a gas compressor for cultivation, and blows air into a cultivation area through the compressed air to meet the cultivation requirement, wherein the gas compressor is a component which utilizes a blade rotating at a high speed to do work for air in a gas turbine engine to improve the air pressure; the front end parts of the blades of the compressor impeller are bent and called guide wheels, and the guide wheels play a role of guiding gas into the working impeller without impact so as to reduce the impact loss of gas flow; the compressor impeller of a small supercharger generally integrates a guide wheel and a working impeller; the outlet of the impeller of the gas compressor is provided with a diffuser, so that the kinetic energy obtained by the gas in the impeller is converted into pressure as much as possible; the diffuser is divided into a blade type diffuser and a slit type diffuser; the shell of the compressor is provided with an air flow inlet and an air flow outlet; the inlet is generally arranged in the direction of the rotor 72, and the flow passage is slightly reduced gradually to reduce the air inlet resistance; the outlet is generally designed into a volute shape with a flow passage gradually expanding along the circumference, so that high-speed airflow is continuously expanded and the total efficiency of the supercharger is improved; the compressor is driven by a turbine, and the main performance parameters of the compressor are as follows: rotational speed, flow, air flow, pressure ratio, efficiency, etc.

Its inside rotor of present breed fan is when high-speed rotation, the physical contact between the radial bearing that the rotor was established rather than the both ends cover is too big, the friction is too big, and simultaneously, because the axial shake can appear when high-speed rotation in the rotor, this kind of axial shake of the unable effectual restriction of current fan, thereby make the rotor also can't further increase the rotational speed, and simultaneously, the thrust dish position also can produce considerable friction heat, current setting does not have fine cooling heat dissipation to the thrust dish, cause equipment to damage easily, the performance of fan has seriously been restricted and the blast air efficiency of calming anger.

Disclosure of Invention

An object of the present invention is to solve at least the above problems and/or disadvantages and to provide at least the advantages described hereinafter. To achieve these objects and other advantages in accordance with the purpose of the invention, there is provided a novel air thrust bearing and a method for manufacturing the same, including:

the middle part of the thrust frame is provided with a thrust disc;

the two ends of the rotor are sleeved with radial bearings, and one end of the rotor penetrates out and is connected with the thrust disc;

cooling foils detachably arranged on two sides of the thrust disc;

and the air floatation foil is detachably arranged in the two radial bearing inner rings.

Preferably, the thrust frame comprises a front thrust pad base plate and a rear thrust pad base plate which are arranged at intervals; the thrust plate is clamped between the front thrust bush chassis and the rear thrust bush chassis to form limit; through holes for penetrating the rotor are respectively formed in the middle of the front thrust lining base plate and the middle of the rear thrust lining base plate; and the front thrust bushing chassis and the rear thrust bushing chassis are both provided with a plurality of air holes.

Preferably, wherein the air foil comprises three radial wave foils; three first clamping grooves with openings at two ends are formed in the inner ring of the radial bearing; each radial wave foil is of a short-piece structure, and one end of each radial wave foil is provided with a first clamping piece corresponding to the first clamping groove; the three radial wave foils are attached to the inner ring of the radial bearing at trisection intervals after being bent, and the three first clamping pieces are respectively embedded into the three first clamping grooves.

Preferably, wherein the air foil further comprises a radial flat foil; the radial flat foil is of a long-piece structure, and one end of the radial flat foil is provided with a second clamping piece corresponding to the first clamping groove; the radial flat foil is completely attached to the inner sides of the three radial wave foils after being integrally rolled, and the second card is embedded into one of the first clamping grooves; the inner side of the radial flat foil after being rolled is evenly abutted and connected with the side face of the front end of the rotor.

Preferably, each radial wave foil is provided with a first wave-shaped flow channel; the first wavy flow channel specifically comprises: a plurality of first U-shaped grooves which are upward arranged in parallel at intervals by taking the first card as a substrate; each radial wave foil is provided with a notch for reducing the strength; the notch is specifically as follows: three cracks which are vertically arranged upwards at intervals by taking the first card as a substrate; the three first clamping grooves are circumferentially arranged in the inner ring of the radial bearing in a trisection manner and are specifically divided into a large clamping groove and two small clamping grooves; the first card and one of the second cards are jointly embedded in the large card slot; the other two second cards are respectively embedded in the two small card slots.

Preferably, wherein the cooling foil comprises a plurality of thrust wave foils; a plurality of second clamping grooves are formed in the front thrust substrate disc in a surrounding mode; each thrust bump foil is of a short fan-ring structure, and one end of each thrust bump foil is provided with a third clamping piece corresponding to the second clamping groove; the plurality of thrust bump foils are uniformly attached to the rear end of the front thrust lining chassis at annular intervals, and each third clamping piece is embedded into the second clamping groove; the front end of the rear thrust bushing chassis is provided with the same structure.

Preferably, wherein the cooling foil further comprises a plurality of thrust flat foils; the plurality of thrust flat foils are of long fan-shaped ring structures, and one ends of the thrust flat foils are provided with fourth clamping pieces corresponding to the second clamping grooves; the plurality of thrust flat foils are uniformly attached to the rear ends of the plurality of thrust wave foils in a surrounding mode, and each fourth card is respectively embedded into the plurality of second clamping grooves; the front end of the rear thrust bushing chassis is provided with the same structure.

Preferably, the third cards of the thrust wave foils are fitted into the second card slots one by one in the clockwise direction; fourth cards of the thrust flat foils are embedded into the second clamping grooves one by one along the anticlockwise direction; the same structure is arranged at the front end of the rear thrust bushing chassis; each thrust wave foil is provided with a second wavy flow channel; the second wavy flow passage includes: a plurality of second U-shaped grooves which are upward arranged in parallel at intervals by taking the third card as a substrate; the depths of the second U-shaped grooves are decreased progressively; each fourth card is provided with a step-shaped flanging edge.

Preferably, the method for manufacturing the novel air thrust bearing is characterized in that,

the method comprises the following steps of firstly, blanking and cutting, and comprises the following processes: cutting the high-temperature alloy steel strip material into the size required by the product by using an automatic cutting machine;

step two, solution treatment, which comprises the following steps: feeding the material subjected to blanking and cutting in the step one into a vacuum furnace, heating to a certain temperature along with the furnace temperature, preserving the heat for a period of time, and then emptying and cooling to enable the mechanical property of the material to meet the requirement required by processing;

step three, pressing corrugation, wherein the process is as follows: pressing the material subjected to the first heat treatment in the step two by using a special pressing die to enable the material to reach the wave shape required by the product, and finely adjusting the wave shape of the material by adjusting the pressure applied by the special pressing die;

step four, aging strengthening, which comprises the following steps: cleaning the material subjected to corrugation pressing in the third step by ultrasonic waves to ensure that the surface of the material is clean and free of impurities, then feeding the material into a vacuum furnace, heating the material to a certain temperature along with the temperature of the furnace, preserving the heat for a period of time, then setting the cooling speed of the vacuum furnace for cooling, and then cooling the material along with the furnace and discharging the material out of the furnace to enable the mechanical property of the material to meet the use requirement;

step five, bending, which comprises the following steps: bending the material subjected to aging strengthening in the fourth step to a required angle of the product by using a finely-adjustable bending clamp;

step six, wire cutting, which comprises the following steps: cutting the material bent in the fifth step into the shape required by the product by using a linear cutting device;

preferably, the high-temperature alloy steel strip material in the first step is GH4169, and the dimensions are as follows: length × width × thickness: 55mm by 40mm by 0.15 mm.

The invention at least comprises the following beneficial effects:

the first key point of the device which is different from the past design is that cooling foils are detachably arranged on two sides of a thrust disc clamped in a thrust frame; the advantage of this kind of structure lies in, the rotor is under high-speed pivoted state, can produce axial and rock, through the thrust dish of being connected after passing one of them journal bearing with the rotor, because the thrust dish centre gripping sets up in thrust frame, thereby the axial limiting displacement to the rotor has been played, can prevent effectively that the axial of rotor from rocking, can further improve the rotational speed of rotor, and after having assembled the cooling foil piece, when the rotor drives thrust dish and rotates, whole thrust dish can produce insufficient support with the cooling foil piece and lean on, not complete planar laminating, thereby the physical contact area of thrust dish has been reduced, play certain cooling and heat dissipation effect, play certain protection to the thrust dish, further guarantee the thrust effect.

The second key point of the device is that the 'air floatation foil' is detachably arranged in the radial bearing inner ring sleeved at the two ends of the rotor in the cylinder of the fan; the structure has the advantages that after the front end of the rotor of the fan is sleeved in the radial bearing, a rigid air film can be generated between the rotor and the air floatation foil along with the high-speed rotation of the rotor, so that the rotor reaches an air floatation state, the physical contact of the rotor under the high-speed rotation is reduced, the abrasion is reduced, the rotating speed of the rotor can be further improved, and the applicability of the device is improved.

Additional advantages, objects, and features of the invention will be set forth in part in the description which follows and in part will become apparent to those having ordinary skill in the art upon examination of the following or may be learned from practice of the invention.

Drawings

FIG. 1 is an assembly view of the overall structure of the present invention;

FIG. 2 is a block diagram of the present invention radial bearing with the air foil attached;

FIG. 3 is a view showing a structure of a radial wave foil in the air foil of the present invention;

FIG. 4 is a view showing a radial flat foil structure in the air foil of the present invention;

FIG. 5 is a side view block diagram of the radial bearing of the present invention;

FIG. 6 is a block diagram of the front thrust pad disk of the present invention fitted with a cooling foil;

FIG. 7 is an overall view of a cooling foil according to the present invention;

FIG. 8 is a detail view of the cooling foil assembly of the present invention;

FIG. 9 is a view showing a structure of a thrust bump foil in the cooling foil of the present invention;

FIG. 10 is a view showing a structure of a thrust flat foil in the cooling foil of the present invention;

Detailed Description

The present invention is further described in detail below with reference to the attached drawings so that those skilled in the art can implement the invention by referring to the description text. It will be understood that terms such as "having," "including," and "comprising," as used herein, do not preclude the presence or addition of one or more other elements or groups thereof. It is to be understood that in the description of the present invention, the terms indicating orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, and are used only for convenience in describing the present invention and for simplification of the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. In the description of the present invention, unless otherwise specifically stated or limited, the terms "mounted," "disposed," "sleeved/connected," "connected," and the like are used broadly, and for example, "connected" may be a fixed connection, a detachable connection, or an integral connection, a mechanical connection, an electrical connection, a direct connection, an indirect connection via an intermediate medium, or a communication between two elements, and those skilled in the art will understand the specific meaning of the terms in the present invention specifically. Further, in the present invention, unless explicitly stated or limited otherwise, reference to a first feature "on" or "under" a second feature can mean that the first and second features are in direct contact, or that the first and second features are in indirect contact via an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature.

Fig. 1-10 illustrate one implementation of the present invention, including:

the middle part of the thrust frame 2 is provided with a thrust disc 21;

a rotor 12, two ends of which are sleeved with radial bearings 7, and one end of which penetrates out and is connected with a thrust disc 21;

cooling foils 6 detachably disposed on both sides of the thrust disk 21;

and an air floatation foil 8 which is detachably arranged in the inner rings of the two radial bearings 7.

The working principle is as follows: when the invention is used, firstly, the whole rotor 12 is assembled in a cylinder of the compressor, when the cylinder is electrified and the rotor 12 rotates at a high speed, two ends of the rotor 12 are embedded in the inner ring of the radial bearing 7 to rotate at a high speed, and at the moment, a layer of rigid air film is formed between the rotor 12 and the inner ring of the radial bearing 7 through the air floatation foil 8 arranged in the radial bearing 7, so that an air floatation supporting effect is provided for two ends of the rotor 12, the physical contact and friction of the rotor 12 under the high-speed rotation are reduced, the rotating speed of the rotor 12 can be further improved, and the high-power operation of the compressor is ensured; secondly, when the rotor 12 drives the thrust disk 21 to rotate at a high speed, a considerable amount of friction heat is generated, and the cooling foil 6 mounted on the thrust frame 2 can reduce the contact area between the thrust disk 21 and the thrust frame 2, so as to reduce friction, so that the thrust disk 21 can radiate heat effectively, and the whole structure is protected to a certain extent.

Transversely placing a machine barrel on a working position, after an external power supply is switched on, starting high-speed rotation of a rotor 12, starting external gas to be introduced into a volute, driving an impeller to rotate at high speed through the rear end of the rotor 12, starting spiral annular diffusion on the gas through the matching of the impeller and the volute, discharging the diffused gas from the output end of the volute, and then introducing the gas into a culture water area to realize oxygen enrichment;

the first key point of the device is different from the past design is that the two sides of the thrust disk 21 clamped in the thrust frame 2 are detachably provided with 'cooling foils 6'; the structure has the advantages that the rotor 12 can generate axial shaking in a high-speed rotating state, the thrust disc 21 is connected with the rotor 12 after penetrating through one radial bearing 7, the thrust disc 21 is clamped in the thrust frame 2, so that the axial limiting effect on the rotor 12 is achieved, the axial shaking of the rotor 12 can be effectively prevented, the rotating speed of the rotor 12 can be further improved, after the cooling foil 6 is assembled, when the rotor 12 drives the thrust disc 21 to rotate, the whole thrust disc 21 can generate abutting against with the cooling foil 6 and is not completely plane attached, the physical contact area of the thrust disc 6 is reduced, a certain cooling and heat dissipation effect is achieved, the thrust disc is protected to a certain extent, and the thrust effect is further guaranteed.

The second key point of the device is that the 'air floatation foil 8' is detachably arranged in the inner ring of the radial bearing 7 sleeved at the two ends of the rotor 12 in the cylinder of the blower; the structure has the advantages that after the front end of the rotor 12 of the fan 1 is sleeved in the radial bearing 7, a rigid air film is generated between the rotor 12 and the air floatation foil 8 along with the high-speed rotation of the rotor 12, so that the rotor 12 reaches an air floatation state, the physical contact of the rotor 12 under the high-speed rotation is reduced, the abrasion is reduced, the rotating speed of the rotor can be further improved, and the applicability of the device is improved.

In the above technical solution, the thrust frame 2 includes two front thrust pad chassis 22 and a rear thrust pad chassis 23 arranged at an interval; the thrust plate 21 is clamped between the front thrust bush base plate 22 and the rear thrust bush base plate 23 to form a limit; the middle parts of the front thrust bush chassis 22 and the rear thrust bush chassis 23 are respectively provided with a through hole for penetrating the rotor 12; the front thrust bushing chassis 22 and the rear thrust bushing chassis 23 are both provided with a plurality of air holes 220.

The working principle is as follows: when the front end of the rotor 12 drives the thrust disc 21 to rotate together, the thrust disc 21 can be clamped and limited by the front thrust bush chassis 22 and the rear thrust bush chassis 23, so that the axial shaking of the rotor 12 is prevented, the rotor 12 can be further improved in rotating speed, and the operation efficiency is improved; when the rotor 12 drives the thrust plate 21 to rotate at a high speed, considerable friction heat is generated, and through the plurality of air holes 220, the cooling foils 6 arranged on the front thrust lining base plate 22 and the rear thrust lining base plate 23 can be effectively radiated, so that the structure is protected to a certain extent.

In the above technical solution, the air floating foil 8 includes three radial bump foils 81; three first clamping grooves 70 with two open ends are formed in the inner ring of the radial bearing 7; each radial bump foil 81 is of a short-piece structure, and one end of each radial bump foil is provided with a first clamping piece 811 corresponding to the first clamping groove 70; the three radial bump foils 81 are attached to the inner ring of the radial bearing 7 at three equal intervals after being bent, and the three first clamping pieces 811 are respectively embedded into the three first clamping grooves 70.

The working principle is as follows: when the three radial wave foils 81 are assembled, the first clamping piece 811 can be directly pushed into the first clamping groove 70 from the opening at one end of the radial bearing 7 in the radial direction, so that the embedding is realized, the assembling difficulty of the radial wave foils 71 is obviously reduced, the assembling is easier and more convenient, the assembling efficiency is improved, and meanwhile, the structure is ensured to be more stable by 7; by using the three radial wave foils 81 to be uniformly attached to the inner ring of the radial bearing 7, the three radial wave foils 81 can achieve a more uniform and complete covering effect on the inner ring of the radial bearing 7, and the functionality of the radial wave foils 81 is further improved.

In the above technical solution, the air foil 8 further includes a radial flat foil 82; the radial flat foil 82 is of a long-sheet structure, and one end of the radial flat foil is provided with a second clamping piece 821 corresponding to the first clamping groove 70; the radial flat foil 82 is completely attached to the inner sides of the three radial corrugated foils 81 after being integrally rolled, and the second card is embedded into one of the first clamping grooves 70; the inner side of the radial flat foil 82 after being rolled is evenly abutted and connected with the side face of the front end of the rotor 12.

The working principle is as follows: when the radial flat foil 82 is assembled, the second clamping piece 821 can be directly pushed into the first clamping groove 70 from the opening at one end of the inner ring of the radial bearing 7 in the radial direction, so that the embedding is realized, the assembling difficulty of the radial flat foil 82 is obviously reduced, the assembling is easier and more convenient, the assembling efficiency is improved, and the structure is ensured to be more stable; the radial flat foil 82 with a long-piece structure is uniformly attached to the inner sides of the three radial wave foils 81, so that the radial flat foil 82 can achieve a more uniform and stable attaching and covering effect on the inner rings formed by the three radial wave foils 81, and the functionality of the radial flat foil 82 is further improved.

In the above technical solution, each radial corrugated foil 81 is provided with a first corrugated flow channel 812; the first wavy flow channel 812 specifically includes: a plurality of first U-shaped grooves 813 are formed upward and in parallel at intervals on the first card 811.

The working principle is as follows: because the front end of the rotor 12 is uniformly sleeved in the whole rolled radial flat foil 82, when the rotor 12 reaches a high rotation speed, airflow rapidly flows through the first U-shaped grooves 813 of the first wavy flow channel 812 to form a plurality of radial airflow channels, and the airflow channels can enable the three radial flat foils 81 to generate an intermittent supporting effect on the inner radial flat foil 82, so that the rolled radial flat foil 82 can generate a certain degree of jitter, and the jitter is matched with high-speed airflow passing through the side surface of the rotor 12, so that a high-quality rigid air film can be generated between the rolled radial flat foil 82 and the side surface of the front end of the rotor 12, thereby achieving an air-flotation supporting effect on the rotor 12, reducing physical contact and friction of the rotor 12 under high-speed rotation, and further improving the rotation speed of the rotor 12.

In the above technical solution, each radial wave foil 81 is provided with a notch 814 for reducing strength; the gap 814 specifically includes: three slits 815 are vertically spaced upward from the first card 811.

The working principle is as follows: by arranging the three cracks 815, the overall strength of the whole radial wave foil 81 can be effectively reduced, so that when the rotor 12 rotates at a high speed, the intermittent contact frequency of the three radial wave foils 81 on the radial flat foil 82 is higher, the shaking effect of the whole radial flat foil 82 is improved, the quality of a rigid air film manufactured between the subsequent radial flat foil 82 and the rotor 12 is improved, the friction can be further reduced, and the air flotation effect of the rotor 12 is improved.

In the above technical solution, the three first locking grooves 70 are circumferentially arranged in the inner ring of the radial bearing 7 in trisection, and are specifically divided into a large locking groove 701 and two small locking grooves 702; the first card 811 and one of the second cards 821 are jointly engaged in the large card slot 701; the other two second cards 821 are respectively fitted into the two small card slots 702.

The working principle is as follows: by arranging a large clamping groove 701, one of the radial bump foil 81 and the radial flat foil 82 can be clamped and embedded into the same first clamping groove (namely, the large clamping groove 701) through the first clamping plate 811 and the second clamping plate 821, so that the integrity of the device is better; the other two small slots 702 can stably fit the first clamping pieces 811 of the other two radial bump foils 81, so that the overall support is ensured.

In the above technical solution, the cooling foil 6 comprises a plurality of thrust bump foils 61; a plurality of second clamping grooves 222 are arranged on the front thrust lining chassis 22 in a surrounding manner; each thrust wave foil 61 is of a short fan-shaped ring structure, and one end of each thrust wave foil is provided with a third clamping piece 611 corresponding to the second clamping groove 222; the thrust bump foils 61 are uniformly attached to the rear end of the front thrust lining chassis 22 at annular intervals, and each third clamping piece 611 is respectively embedded in the second clamping groove 222; the front end of the rear thrust washer chassis 23 is provided with the same structure as described above.

The working principle is as follows: when a plurality of thrust wave foils 61 are assembled, the thrust wave foils can be directly embedded into a plurality of second clamping grooves 222 one by one through the third clamping pieces 611, so that the assembly difficulty of the thrust wave foils 61 is remarkably reduced, the assembly is easier and more convenient, the assembly efficiency is improved, and the labor intensity is reduced; meanwhile, the integral structure is ensured to be more stable; the thrust bump foil 61 of a plurality of short fan ring structures can be more stably and uniformly attached to the whole annular front thrust lining chassis 22, the covering effect is better, and the functionality of the structure is further improved.

In the above technical solution, the cooling foil 6 further includes a plurality of thrust flat foils 62; the thrust flat foils 62 are long fan-ring structures, and one end of each thrust flat foil 62 is provided with a fourth card 621 corresponding to the second card slot 222; the plurality of anti-thrust flat foils 62 are uniformly attached to the rear ends of the plurality of anti-thrust wave foils 61 in a surrounding manner, and each fourth card 621 is respectively embedded into the plurality of second clamping grooves 222; the front end of the rear thrust washer chassis 23 is provided with the same structure as described above.

The working principle is as follows: when the plurality of thrust flat foils 62 are assembled, the thrust flat foils 62 can be directly embedded into the plurality of second clamping grooves 222 one by one through the fourth clamping pieces 621, so that the assembling difficulty of the thrust flat foils 62 is obviously reduced, the assembly is easier and more convenient, the assembling efficiency is improved, the labor intensity is reduced, and the structure is ensured to be more stable; the thrust flat foils 62 of the long fan-ring structures can be more stably and uniformly attached to the convex surfaces of the thrust wave foils 61, the covering effect is better, and the functionality of the structure is further improved.

In the above technical solution, the third tabs 611 of the thrust wave foils 61 are fitted into the second slots 222 one by one in the clockwise direction; the fourth cards 621 of the thrust flat foils 62 are fitted into the second card slots 222 one by one in the counterclockwise direction; the front end of the rear thrust pad chassis 23 is provided with the same structure as described above.

The working principle is as follows: the thrust wave foils and the thrust flat foils are arranged in an opposite clockwise sequence, so that the rotation direction of the thrust wave foils and the rotation direction of the rotor can be synchronized, and friction is reduced; simultaneously, third card and fourth card lean on the back each other and jointly gomphosis to the second draw-in groove for the wholeness of device is better, has promoted the stability of device structure.

In the above technical solution, each thrust wave foil 61 is provided with a second wavy flow channel 612; the second wavy flow passage 612 includes: a plurality of second U-shaped grooves 613 which are upward arranged in parallel at intervals and take the third card 611 as a substrate; the depth of the second U-shaped grooves 613 decreases; each of the fourth cards 621 is provided with a stepped folded edge 622.

The working principle is as follows: the second U-shaped grooves 613 with gradually decreased depth can enable the joint surface of the whole thrust wave foil 61 and the thrust flat foil 62 to form an inclined surface, so that the joint between the parts is tighter, and the friction can be further reduced when the whole device is contacted with the thrust disc 21 rotating at high speed after being assembled; the stepped flanging 614 provides a certain reserved space, so that when the rotor 12 rotates with the thrust disk 21, scraping can be reduced, and a certain protection effect can be achieved.

Example 1:

a novel thrust bearing preparation method comprises the following steps:

the method comprises the following steps of firstly, blanking and cutting, and comprises the following processes: cutting a high-temperature alloy steel strip material (GH4169) into the required size (length multiplied by width multiplied by thickness: 55mm multiplied by 40mm multiplied by 0.15mm) of a product by using an automatic cutting machine;

step two, solution treatment, which comprises the following steps: feeding the material subjected to blanking and cutting in the step one into a vacuum furnace, heating to a certain temperature (1050 ℃) along with the furnace temperature, preserving the heat for a period of time (1h), and then emptying and cooling (observing by a metallographic instrument, cooling the material until the grain diameter of a grain structure is increased to 45 mu m), so that the mechanical property of the material meets the requirement for processing;

step four, aging strengthening, which comprises the following steps: cleaning the material subjected to corrugation pressing in the third step by ultrasonic waves, keeping the surface of the material clean and free of impurities, then feeding the material into a vacuum furnace, heating the material to a certain temperature (720 ℃) along with the temperature of the furnace, keeping the temperature for a period of time (8h), then setting the cooling speed of the vacuum furnace (cooling to 620 ℃ at a speed of 50 ℃/h, keeping the temperature for 8h), cooling the material along with the furnace until the temperature is lower than (100 ℃) and discharging the material out of the furnace, so that the mechanical property of the material meets the use requirement;

step five, bending, which comprises the following steps: bending the material subjected to aging strengthening in the fourth step to a required angle of the product by using a finely-adjustable bending clamp (namely, bending the first card 811, the second card 821, the third card 611 and the fourth card 621);

step six, wire cutting, which comprises the following steps: and (5) cutting the material subjected to bending in the fifth step into the shape required by the product by using a wire cutting device (setting the processing parameters of wire cutting according to actual requirements of the whole material, and cutting the material into one of radial wave foil 81, radial flat foil 82, thrust wave foil 61 and thrust flat foil 62).

In example 1:

in the first step, a GH4169 high-temperature alloy steel strip material is selected, and the GH4169 is an aviation material, so that the GH4169 high-temperature alloy steel strip material is not easy to deform at high temperature and can keep certain strength at the high temperature, and the GH4169 high-temperature alloy steel strip material can better adapt to the friction high temperature of a rotor at ultrahigh rotating speed;

meanwhile, the material is cut into the size (length multiplied by width multiplied by thickness: 55mm multiplied by 40mm multiplied by 0.15mm) because GH4169 is expensive, the size can be maximally adapted to the processing requirements of foils with four different shapes and specifications (radial bump foil 81, radial flat foil 82, thrust bump foil 61 and thrust flat foil 62), and meanwhile, the residual material of the subsequent processing is less, and the production cost is reduced.

In the second step, through the solution treatment set by the parameters, the tensile strength of the whole material after treatment is not less than 965MPa, the yield strength is not less than 550MPa, the elongation is not less than 30 percent, even if the mechanical strength of the material meets the processing requirements;

in the third step, the first wavy flow passage 812 and the second wavy flow passage 612 can be stably pressed and processed on the radial wave foil 81 and the thrust wave foil 61 by corrugating, and meanwhile, the plurality of second U-shaped groove pressures 613 in the second wavy flow passage 612 can be synthesized into different depths by controlling the applied pressure of the pressing die, so that the processing requirement is met.

In the fourth step, the setting of the parameters is used for aging strengthening, so that the Rockwell hardness HRC of the whole material after treatment is more than 42, the tensile strength is more than or equal to 1275Mpa, the yield strength is more than or equal to 1035Mpa, the elongation is more than or equal to 12%, the delta metallographic phase in the whole material is reduced, the strength and the impact property of the material are increased, the good wear resistance of the material in the working condition and the no deformation at the temperature of 300 ℃ are ensured, and even if the mechanical strength of the material meets the use requirements;

in the fifth step, the finely adjustable bending fixture is convenient to operate and control, and stable and accurate bending processing can be performed on the first card 811, the second card 821, the third card 611 and the fourth card 621.

In the sixth step, the linear cutting is convenient and controllable, and the material can be stably cut into one of (radial wave foil 81, radial flat foil 82, thrust wave foil 61 and thrust flat foil 62) according to production requirements.

The number of apparatuses and the scale of the process described herein are intended to simplify the description of the present invention. Applications, modifications and variations of the present invention will be apparent to those skilled in the art. While embodiments of the invention have been described above, it is not limited to the applications set forth in the description and the embodiments, which are fully applicable in various fields of endeavor to which the invention pertains, and further modifications may readily be made by those skilled in the art, it being understood that the invention is not limited to the details shown and described herein without departing from the general concept defined by the appended claims and their equivalents.

Claims

1. A novel air thrust bearing, comprising:

the middle part of the thrust frame is provided with a thrust disc;

cooling foils detachably arranged on two sides of the thrust disc;

2. The novel air thrust bearing as claimed in claim 1, wherein said thrust frame includes two spaced apart forward thrust pad segments and a rear thrust pad segment; the thrust plate is clamped between the front thrust bush chassis and the rear thrust bush chassis to form limit; through holes for penetrating the rotor are respectively formed in the middle of the front thrust lining base plate and the middle of the rear thrust lining base plate; the front thrust bushing chassis and the rear thrust bushing chassis are both provided with a plurality of air holes.

3. The novel airfoil thrust bearing of claim 1, wherein said airfoil foil includes three radial bump foils; three first clamping grooves with openings at two ends are formed in the inner ring of the radial bearing; each radial wave foil is of a short-piece structure, and one end of each radial wave foil is provided with a first clamping piece corresponding to the first clamping groove; the three radial wave foils are attached to the inner ring of the radial bearing at trisection intervals after being bent, and the three first clamping pieces are respectively embedded into the three first clamping grooves.

4. The novel airfoil thrust bearing of claim 3, wherein said airfoil foil further comprises a radially flat foil; the radial flat foil is of a long-sheet structure, and one end of the radial flat foil is provided with a second clamping sheet corresponding to the first clamping groove; the radial flat foil is completely attached to the inner sides of the three radial wave foils after being integrally rolled, and the second card is embedded into one of the first clamping grooves; the inner side of the radial flat foil after being rolled is evenly abutted and connected with the side face of the front end of the rotor.

5. The novel air thrust bearing as claimed in claim 4, wherein each of said radial corrugated foils is provided with a first corrugated flow passage; the first wavy flow channel specifically comprises: a plurality of first U-shaped grooves which are upward arranged in parallel at intervals by taking the first card as a substrate; each radial wave foil is provided with a notch for reducing the strength; the notch is specifically as follows: three cracks which are vertically arranged upwards at intervals by taking the first card as a substrate; the three first clamping grooves are circumferentially arranged in the inner ring of the radial bearing in a trisection manner and are specifically divided into a large clamping groove and two small clamping grooves; the first card and one of the second cards are jointly embedded in the large card slot; the other two second cards are respectively embedded in the two small card slots.

6. The novel airfoil thrust bearing of claim 1, wherein said cooling foil comprises a plurality of thrust bump foils; a plurality of second clamping grooves are formed in the front thrust substrate disc in a surrounding mode; each thrust bump foil is of a short fan-ring structure, and one end of each thrust bump foil is provided with a third clamping piece corresponding to the second clamping groove; the plurality of thrust bump foils are uniformly attached to the rear end of the front thrust lining chassis at annular intervals, and each third clamping piece is embedded into the second clamping groove; the front end of the rear thrust bushing chassis is provided with the same structure.

7. The novel airfoil thrust bearing of claim 6, wherein said cooling foil further comprises a plurality of thrust flat foils; the plurality of thrust flat foils are of long fan-shaped ring structures, and one ends of the thrust flat foils are provided with fourth clamping pieces corresponding to the second clamping grooves; the plurality of thrust flat foils are uniformly attached to the rear ends of the plurality of thrust wave foils in a surrounding mode, and each fourth card is respectively embedded into the plurality of second clamping grooves; the front end of the rear thrust bushing chassis is provided with the same structure.

8. The novel air thrust bearing as claimed in claim 7, wherein the third locking pieces of the thrust bump foils are respectively fitted into the second locking grooves one by one in a clockwise direction; fourth cards of the thrust flat foils are embedded into the second clamping grooves one by one along the anticlockwise direction; the same structure is arranged at the front end of the rear thrust lining chassis; each thrust wave foil is provided with a second wavy flow channel; the second wavy flow passage includes: a plurality of second U-shaped grooves which are upward arranged in parallel at intervals by taking the third card as a substrate; the depths of the second U-shaped grooves are decreased progressively; each fourth card is provided with a step-shaped flanging edge.

9. The method as claimed in any one of claims 1 to 8, wherein the thrust bearing is a thrust bearing,

step five, bending, which comprises the following steps: bending the material subjected to aging strengthening in the fourth step to a required angle of a product by using a finely-adjustable bending clamp;

step six, wire cutting, which comprises the following steps: and D, cutting the material bent in the step five into the shape required by the product by using a linear cutting device.

10. The method for manufacturing the novel air thrust bearing as claimed in claim 9, wherein the high temperature alloy steel strip in the first step is made of GH4169 with the following dimensions: length × width × thickness: 55mm by 40mm by 0.15 mm.