CN113775533B - Turbopump device for rocket engine - Google Patents
Turbopump device for rocket engine Download PDFInfo
- Publication number
- CN113775533B CN113775533B CN202111081709.5A CN202111081709A CN113775533B CN 113775533 B CN113775533 B CN 113775533B CN 202111081709 A CN202111081709 A CN 202111081709A CN 113775533 B CN113775533 B CN 113775533B
- Authority
- CN
- China
- Prior art keywords
- blade
- shaft
- diffuser
- left end
- hub
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000001125 extrusion Methods 0.000 claims abstract description 10
- 230000006698 induction Effects 0.000 claims abstract description 7
- 239000000411 inducer Substances 0.000 claims description 12
- 239000007788 liquid Substances 0.000 claims description 7
- 238000002485 combustion reaction Methods 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 238000005507 spraying Methods 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 7
- 230000001939 inductive effect Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 239000000243 solution Substances 0.000 description 2
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
-
- 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
- F04D29/053—Shafts
-
- 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
- F04D29/053—Shafts
- F04D29/054—Arrangements for joining or assembling shafts
-
- 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
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
-
- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a turbine pump device for a rocket engine, which comprises a shell (1), a centrifugal impeller (2) and a connecting shaft assembly (3), wherein main blades and spiral induction blades are arranged on the periphery of a hub, and the turbine pump device is characterized in that: the connecting shaft assembly comprises a first shaft (31) and a second shaft (32), wherein the left end of the first shaft is provided with a step part (37), the step part is inserted into a corresponding step hole of the hub, the left end of the first shaft is provided with a first threaded hole, a first screw rod (33) is connected in the first threaded hole, the left end of the first screw rod is provided with a shoulder head part (36), the shoulder head part is provided with an extrusion conical surface (38), the second threaded hole is connected with a second screw rod (34), and the left end of the second screw rod is connected with a diversion cap (35). The invention has the advantages of high connection strength and convenient installation/disassembly; by means of the design of the grooves and/or the auxiliary guide vanes, the pressure loss of the diffuser can be reduced, and therefore the outlet pressure of the turbine pump is improved.
Description
Technical Field
The invention relates to the technical field of rocket engines, in particular to a turbine pump device for a rocket engine.
Background
The turbine pump of rocket engine is mainly composed of inducer, centrifugal impeller, mechanical seal, bearing, shafting supporting system and shell. However, the existing turbine pump device has the problems of insufficient impeller mounting strength, inconvenient mounting/dismounting and larger pump outlet pressure loss.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provide a turbine pump device for a rocket engine, which has the advantages of high connection strength and convenient installation/disassembly compared with the existing impeller installation structure through the design of a connecting shaft assembly. Through the design of the grooves and/or the auxiliary guide vanes, the pressure loss of the diffuser can be reduced, and liquid flow orderly flows to the outlet pipe of the volute, so that the outlet pressure of the turbine pump is improved, and the power loss of the turbine pump is reduced.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows:
the utility model provides a turbopump device for rocket engine, it includes casing (1), centrifugal impeller (2), connecting axle subassembly (3), and centrifugal impeller is installed to the pump intracavity of casing, and centrifugal impeller passes through connecting axle subassembly to be installed on the casing, and centrifugal impeller includes wheel hub (21), and wheel hub's periphery is equipped with main blade (22), spiral induction blade (23), and spiral induction blade is located the upper reaches of main blade, its characterized in that: the connecting shaft assembly (3) comprises a first shaft (31) and a second shaft (32), wherein the left end of the second shaft is inserted into a stepped concave hole at the right end of the first shaft, the right end of the second shaft is connected with a combustion part or an injection part of an engine, the left end of the first shaft is provided with a stepped part (37), the stepped part is inserted into a corresponding stepped hole of a hub, the left end of the first shaft is provided with a first threaded hole, the first threaded hole is connected with a first screw (33), the left end of the first screw is provided with a shoulder part (36), the shoulder part is provided with an extrusion conical surface (38), the extrusion conical surface is matched with a corresponding conical surface of the hub, the right end of the first screw is provided with a second threaded hole, the second threaded hole is connected with a second screw (34), and the left end of the second screw is connected with a flow guiding cap (35).
Further, a connecting cavity (24) is formed in the left end of the hub (21), the shoulder head (36) and the second screw (34) are located in the connecting cavity, a key groove and a connecting key (25) are formed in the periphery of the first shaft (31), the first shaft is connected with the hub through the connecting key, and a conical surface of the hub matched with the extrusion conical surface (38) is arranged adjacent to the step concave hole.
Further, the pump chamber of casing (1) has preceding lateral wall (11), back lateral wall (12) of relative setting, is provided with diffuser stator (13) between preceding lateral wall and the back lateral wall, and a plurality of diffuser stator are along circumference evenly distributed, and the diffuser stator is located the radial outside of centrifugal impeller (2), and preceding lateral wall, back lateral wall are including first tilting portion (14), protruding portion (16), second tilting portion (15) that connect gradually, and first tilting portion, protruding portion, second tilting portion are along radial connecting gradually, are provided with recess (17) on back lateral wall (12) between the adjacent diffuser stator, and the recess is formed with sunken mode removal material.
Further, one or more auxiliary guide vanes (18) are arranged in the groove (17).
Further, the radially inner and radially outer ends of the groove (17) are both arcuate portions.
Further, the axial depth of the groove (17) increases gradually from the radially inner end to the radially outer end.
Further, two auxiliary guide vanes (18) are arranged between adjacent diffuser guide vanes (13), the inner radius of each auxiliary guide vane is equal to the inner radius of each diffuser guide vane, and the outer radius of each auxiliary guide vane is unequal to the outer radius of each diffuser guide vane; and the diffuser vane has an outer radius R, the auxiliary vane has an outer radius R1, R1 < R, and r1= (0.70-0.97) R.
Further, the blade profile of the diffuser guide vane (13) is different from the blade profile of the auxiliary guide vane (18), the thickness of the blade of the diffuser guide vane is gradually increased along the direction of liquid flow, and the blade of the auxiliary guide vane is an equal-thickness blade.
Further, the inducer comprises spiral inducing blades (23), each spiral inducing blade comprises a plurality of first spiral blades (231) and a plurality of split spiral blades (232), each split spiral blade is arranged between the corresponding first spiral blades, the blade inlet angle of each split spiral blade is larger than that of each first spiral blade, the blade outlet angle of each split spiral blade is larger than that of each first spiral blade, and the size relationship is 1.05-1.3 times.
Compared with the existing impeller mounting structure, the turbopump device for the rocket engine has the advantages of high connection strength and convenience in mounting/dismounting through the design of the connecting shaft assembly. Through the design of the grooves and/or the auxiliary guide vanes, the pressure loss of the diffuser can be reduced, and liquid flow orderly flows to the outlet pipe of the volute, so that the outlet pressure of the turbine pump is improved, and the power loss of the turbine pump is reduced. The inducer provided by the invention has the advantages that the diversion helical blades are independently designed in a biased way, the inlet and outlet angles of the diversion blades are slightly larger than those of the first helical blade, the effect of preventing the inlet blade of the inducer from being blocked can be achieved, and the total lift effect of the inducer can be improved.
Drawings
FIG. 1 is a schematic view of a turbopump apparatus (partial block diagram of a turbopump) for a rocket engine according to the present invention;
FIG. 2 is a schematic view of a partial enlarged construction of a turbopump apparatus for a rocket engine according to the present invention;
FIG. 3 is a schematic side view of a turbopump apparatus for a rocket engine according to the present invention;
FIG. 4 is a schematic view of the inducer structure of the turbopump device for rocket engines of the present invention.
In the figure: the centrifugal impeller 2, the connecting shaft assembly 3, the front side wall 11, the rear side wall 12, the diffuser vane 13, the first inclined portion 14, the second inclined portion 15, the boss 16, the groove 17, the auxiliary vane 18, the hub 21, the main vane 22, the spiral inducing vane 23, the connecting cavity 24, the connecting key 25, the first shaft 31, the second shaft 32, the first screw 33, the second screw 34, the deflector cap 35, the shoulder portion 36, the step portion 37, the extrusion tapered surface 38, the first spiral vane 231, the shunt spiral vane 232.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention is described in further detail below with reference to the accompanying drawings.
As shown in fig. 1 to 4, a turbo pump device for a rocket engine comprises a casing 1, a centrifugal impeller 2 and a connecting shaft assembly 3, wherein the centrifugal impeller 2 is installed in a pump cavity of the casing 1, the centrifugal impeller 2 is installed on the casing 1 through the connecting shaft assembly 3, the centrifugal impeller 2 comprises a hub 21, a main blade 22 and a spiral induction blade 23 are arranged on the periphery of the hub 21, and the spiral induction blade 23 is positioned on the upstream of the main blade 22, and the turbo pump device is characterized in that: the connecting shaft assembly 3 comprises a first shaft 31 and a second shaft 32, wherein the left end of the second shaft 32 is inserted into a stepped concave hole at the right end of the first shaft 31, the right end of the second shaft 32 is connected with a combustion part or a jet part of an engine, the left end of the first shaft 31 is provided with a stepped part 37, the stepped part 37 is inserted into a corresponding stepped hole of a hub 21, the left end of the first shaft 31 is provided with a first threaded hole, the first threaded hole is connected with a first screw 33, the left end of the first screw 33 is provided with a shoulder part 36, the shoulder part 36 is provided with an extrusion conical surface 38, the extrusion conical surface 38 is matched with a corresponding conical surface of the hub 21, the right end of the first screw 33 is provided with a second threaded hole, the second threaded hole is connected with a second screw 34, the left end of the second screw 34 is connected with a flow guide cap 35, the left end of the hub 21 is provided with a connecting cavity 24, the shoulder part 36 and the second screw 34 are positioned in the connecting cavity 24, the periphery of the first shaft 31 is provided with a key groove and a connecting key 25, the first shaft 31 is connected with the hub 21 through the connecting key 25, the conical surface 38 is matched with the conical surface of the hub 21, and the conical surface of the hub 21 is adjacent to the concave hole.
The centrifugal impeller 2 is a semi-open impeller, and the turbine pump is used for pumping liquid fuel such as low-temperature methane or low-temperature liquid oxygen.
The turbopump device for the rocket engine has the advantages of high connection strength and convenient installation/disassembly compared with the existing impeller installation structure through the design of the connecting shaft assembly 3.
The first screw 33 and the deflector cap 35 are provided with wrench grooves for wrench tool operation.
Further, as shown in fig. 2-3, the pump cavity of the casing 1 has a front side wall 11 and a rear side wall 12 which are oppositely arranged, a diffuser vane 13 is arranged between the front side wall 11 and the rear side wall 12, a plurality of diffuser vanes 13 are uniformly distributed along the circumferential direction, the diffuser vanes 13 are positioned on the radial outer side of the centrifugal impeller 2, the front side wall 11 and the rear side wall 12 comprise a first inclined part 14, a protruding part 16 and a second inclined part 15 which are sequentially connected in sequence, the first inclined part 14, the protruding part 16 and the second inclined part 15 are sequentially connected in the radial direction, a groove 17 is arranged on the rear side wall 12 between the adjacent diffuser vanes 13, the groove 17 is formed in a recessed manner to remove materials, and one or more auxiliary vanes 18 are arranged in the groove 17.
According to the turbopump device for the rocket engine, through the design of the grooves 17 and/or the auxiliary guide vanes 18, the pressure loss of a diffuser can be reduced, and liquid flow orderly flows to the outlet pipe of the volute, so that the outlet pressure of the turbopump is increased, and the power loss of the turbopump is reduced.
Further, the radial inner end and the radial outer end of the groove 17 are arc-shaped parts, so that a better flow guiding effect is achieved.
Further, the axial depth of the groove 17 gradually increases from the radially inner end to the radially outer end, enabling further reduction of the pressure loss of the diffuser.
Further, two auxiliary guide vanes 18 are arranged between adjacent diffuser guide vanes 13, the inner radius of each auxiliary guide vane 18 is equal to the inner radius of each diffuser guide vane 13, and the outer radius of each auxiliary guide vane 18 is unequal to the outer radius of each diffuser guide vane 13; the diffuser vane 13 has an outer radius R and the auxiliary vane 18 has an outer radius R1, R1 < R, r1= (0.80-0.95) R, preferably r1=0.85-0.90R.
The blade profile of the diffuser vane 13 is different from the blade profile of the auxiliary vane 18, the thickness of the blades of the diffuser vane 13 gradually increases along the flow, and the blades of the auxiliary vane 18 are equal thickness blades.
As shown in fig. 4, the inducer includes spiral inducing blades 23, the spiral inducing blades 23 including a plurality of first spiral blades 231, a plurality of diverting spiral blades 232, the diverting spiral blades 232 being disposed between the first spiral blades 231; the blade inlet angle of the splitter screw blade 232 is slightly greater than the blade inlet angle of the first screw blade 231 and the blade outlet angle of the splitter screw blade 232 is slightly greater than the blade outlet angle of the first screw blade 231, e.g., a 1.05-1.3 fold relationship. The inducer of the invention independently designs the diversion helical blades 232 in a biased way, the inlet and outlet angles of the diversion helical blades 232 are slightly larger than those of the first helical blades 231, thus playing a role in preventing the inlet blades of the inducer from being blocked, and improving the total lift effect of the inducer.
The turbopump device for the rocket engine has the advantages of high connection strength and convenient installation/disassembly compared with the existing impeller installation structure through the design of the connecting shaft assembly 3. By the design of the grooves 17 and/or the auxiliary guide vanes 18, the pressure loss of the diffuser can be reduced, and liquid flow orderly flows to the outlet pipe of the volute, so that the outlet pressure of the turbine pump is improved, and the power loss of the turbine pump is reduced.
The above-described embodiments are illustrative of the present invention and are not intended to be limiting, and it is to be understood that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the spirit and scope of the present invention as defined by the appended claims and their equivalents.
Claims (4)
1. The utility model provides a turbopump device for rocket engine, it includes casing (1), centrifugal impeller (2), connecting axle subassembly (3), and centrifugal impeller is installed to the pump intracavity of casing, and centrifugal impeller passes through connecting axle subassembly to be installed on the casing, and centrifugal impeller includes wheel hub (21), and wheel hub's periphery is equipped with main blade (22), spiral induction blade (23), and spiral induction blade is located the upper reaches of main blade, its characterized in that: the connecting shaft assembly (3) comprises a first shaft (31) and a second shaft (32), wherein the left end of the second shaft is inserted into a stepped concave hole at the right end of the first shaft, the right end of the second shaft is connected with a combustion part or a spraying part of an engine, the left end of the first shaft is provided with a stepped part (37), the stepped part is inserted into a corresponding stepped hole of a hub, the left end of the first shaft is provided with a first threaded hole, the first threaded hole is connected with a first screw rod (33), the left end of the first screw rod is provided with a shoulder part (36), the shoulder part is provided with an extrusion conical surface (38), the extrusion conical surface is matched with a corresponding conical surface of the hub, the left end of the first screw rod is provided with a second threaded hole, the second threaded hole is connected with a second screw rod (34), and the left end of the second screw rod is connected with a flow guide cap (35);
the pump cavity of the shell (1) is provided with a front side wall (11) and a rear side wall (12) which are oppositely arranged, diffuser guide vanes (13) are arranged between the front side wall and the rear side wall, the diffuser guide vanes are uniformly distributed along the circumferential direction, the diffuser guide vanes are positioned on the radial outer side of the centrifugal impeller (2), the front side wall and the rear side wall comprise a first inclined part (14), a protruding part (16) and a second inclined part (15) which are sequentially connected, the first inclined part, the protruding part and the second inclined part are sequentially connected along the radial direction, a groove (17) is formed in the rear side wall (12) between the adjacent diffuser guide vanes, and the groove is formed in a material removing way in a concave manner; one or more auxiliary guide vanes (18) are arranged in the groove (17); the radial inner end and the radial outer end of the groove (17) are arc-shaped parts; the axial depth of the groove (17) gradually increases from the radial inner end to the radial outer end; the blade profile of the diffuser guide vane (13) is different from that of the auxiliary guide vane (18), the thickness of the blade of the diffuser guide vane is gradually increased along the direction of liquid flow, and the blade of the auxiliary guide vane is an equal-thickness blade.
2. A turbopump device for rocket engines according to claim 1, characterized in that the left end of the hub (21) is provided with a connecting cavity (24), the shoulder head (36) and the second screw (34) are located in the connecting cavity, the periphery of the first shaft (31) is provided with a key slot and a connecting key (25), the first shaft is connected with the hub through the connecting key, and the conical surface of the hub matched with the extrusion conical surface (38) is arranged adjacent to the stepped concave hole.
3. A turbopump device for rocket engines according to claim 2, characterized in that two auxiliary vanes (18) are arranged between adjacent diffuser vanes (13), the inner radius of which is equal to the inner radius of the diffuser vanes, and the outer radius of which is unequal to the outer radius of the diffuser vanes; and the diffuser vane has an outer radius R, the auxiliary vane has an outer radius R1, R1 < R, and r1= (0.70-0.97) R.
4. A turbopump device for rocket engines according to claim 2 or 3, characterized in that the inducer comprises a spiral inducer blade (23) comprising a plurality of first spiral blades (231), a plurality of splitter spiral blades (232) arranged between the first spiral blades, the splitter spiral blades having a blade inlet angle greater than the blade inlet angle of the first spiral blades, the splitter spiral blades having a blade outlet angle greater than the blade outlet angle of the first spiral blades, and the size relationship being 1.05-1.3 times.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111081709.5A CN113775533B (en) | 2021-09-15 | 2021-09-15 | Turbopump device for rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111081709.5A CN113775533B (en) | 2021-09-15 | 2021-09-15 | Turbopump device for rocket engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113775533A CN113775533A (en) | 2021-12-10 |
| CN113775533B true CN113775533B (en) | 2024-02-20 |
Family
ID=78844239
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111081709.5A Active CN113775533B (en) | 2021-09-15 | 2021-09-15 | Turbopump device for rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113775533B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116335948B (en) * | 2023-04-28 | 2024-03-08 | 江苏大学流体机械温岭研究院 | Fire pump for fire extinguishing system |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1267023A (en) * | 1969-07-31 | 1972-03-15 | ||
| JPH06288398A (en) * | 1993-04-07 | 1994-10-11 | Hitachi Ltd | Centrifugal compressor |
| CN101865160A (en) * | 2010-07-08 | 2010-10-20 | 中国航天科技集团公司第六研究院第十一研究所 | Partial emission pump with low specific speed |
| CN202220750U (en) * | 2011-08-11 | 2012-05-16 | 广东省佛山水泵厂有限公司 | Loosing protection and sealing combined device of impeller nut |
| CN202628618U (en) * | 2012-03-08 | 2012-12-26 | 江苏大学 | AP1000 nuclear main pump with inducer with long and short blades |
| EP2929161A1 (en) * | 2012-12-04 | 2015-10-14 | Thy Engineering | Centrifugal gas compressor or pump comprising a toothed ring and a cowl |
| CN108869333A (en) * | 2018-07-16 | 2018-11-23 | 大连碧蓝节能环保科技有限公司 | Helical blade air pressing type centrifugal blower |
-
2021
- 2021-09-15 CN CN202111081709.5A patent/CN113775533B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1267023A (en) * | 1969-07-31 | 1972-03-15 | ||
| JPH06288398A (en) * | 1993-04-07 | 1994-10-11 | Hitachi Ltd | Centrifugal compressor |
| CN101865160A (en) * | 2010-07-08 | 2010-10-20 | 中国航天科技集团公司第六研究院第十一研究所 | Partial emission pump with low specific speed |
| CN202220750U (en) * | 2011-08-11 | 2012-05-16 | 广东省佛山水泵厂有限公司 | Loosing protection and sealing combined device of impeller nut |
| CN202628618U (en) * | 2012-03-08 | 2012-12-26 | 江苏大学 | AP1000 nuclear main pump with inducer with long and short blades |
| EP2929161A1 (en) * | 2012-12-04 | 2015-10-14 | Thy Engineering | Centrifugal gas compressor or pump comprising a toothed ring and a cowl |
| CN108869333A (en) * | 2018-07-16 | 2018-11-23 | 大连碧蓝节能环保科技有限公司 | Helical blade air pressing type centrifugal blower |
Non-Patent Citations (1)
| Title |
|---|
| 液体火箭发动机推进剂泵诱导轮与离心轮的匹配;杨宝锋;航空学报;20190525;1-12 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113775533A (en) | 2021-12-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8845269B2 (en) | Compressor casing with optimized cavities | |
| US7686586B2 (en) | Compressor | |
| CN1869407B (en) | Compressor wheel | |
| US8414249B2 (en) | Multistage compressor with improved map width performance | |
| US10527059B2 (en) | Turbomachine diffuser | |
| CN102287398A (en) | Small-sized high-speed centrifugal pump suitable for flow regulation in wide range | |
| CN113775533B (en) | Turbopump device for rocket engine | |
| CN105134666A (en) | Anti-cavitation centrifugal pump | |
| CN108361205A (en) | A kind of centrifugal pump impeller and the LNG immersed pumps comprising the centrifugal pump impeller | |
| CN113882971B (en) | Stator guide vane structure of rocket engine turbopump | |
| JP2003511596A (en) | Centrifugal pump | |
| CN112648230B (en) | High-efficiency cavitation-resistant centrifugal pump impeller | |
| CN110159538B (en) | Centrifugal pump device for water pipe system | |
| CN117823450A (en) | Spiral mixed flow pump design method | |
| CN115681170A (en) | High-performance electric water pump for automobile | |
| CN206221284U (en) | Double feed inlet guide-vane horizontal space multi-stage centrifugal pump | |
| CN113775565B (en) | Impeller structure of rocket engine turbopump | |
| US3260216A (en) | Venturi-centrifugal pump | |
| CN205089696U (en) | Anti -cavitation centrifugal pump | |
| JP2001082392A (en) | Turbo machine and pumping plant using the machine | |
| CN115217788B (en) | Inducer-space guide vane applied to high-speed centrifugal pump and design method thereof | |
| CN113775560B (en) | Sealing structure of rocket engine turbine pump | |
| CN112922861B (en) | Compact low-rotation-speed centrifugal compressor | |
| CN219865610U (en) | Diffuser, turbocharger and engine | |
| CN117989173A (en) | Hydraulic pump |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |