CN110332019B - Built-in locking gas floating rotor of closed circulation turbine power generation system - Google Patents
Built-in locking gas floating rotor of closed circulation turbine power generation system Download PDFInfo
- Publication number
- CN110332019B CN110332019B CN201910647952.5A CN201910647952A CN110332019B CN 110332019 B CN110332019 B CN 110332019B CN 201910647952 A CN201910647952 A CN 201910647952A CN 110332019 B CN110332019 B CN 110332019B
- Authority
- CN
- China
- Prior art keywords
- shaft sleeve
- rotor
- turbine
- assembling
- motor shaft
- 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
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/08—Adaptations for driving, or combinations with, pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D25/00—Pumping installations or systems
- F04D25/02—Units comprising pumps and their driving means
- F04D25/04—Units comprising pumps and their driving means the pump being fluid-driven
- F04D25/045—Units comprising pumps and their driving means the pump being fluid-driven the pump wheel carrying the fluid driving means, e.g. turbine blades
-
- 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
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid 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
-
- 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
- F04D29/266—Rotors specially for elastic fluids mounting compressor rotors on 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
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/601—Mounting; Assembling; Disassembling specially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
Abstract
The invention relates to a built-in locking gas floating rotor of a closed circulation turbine power generation system, which comprises a gas compressor impeller, a locking ring, a composite shaft sleeve, a connecting bearing, a transition shaft sleeve, a motor shaft, a fixed shaft sleeve, a radial shaft sleeve and a turbine rotor. The novel motor shaft is characterized in that a threaded hole is formed in the center of the compressor impeller, an annular end face matched with the axial thrust bearing is arranged on the composite shaft sleeve, an inner cylindrical surface assembled with the compressor impeller is sleeved on the connecting shaft sleeve, the motor shaft is formed by assembling a magnetic core and a motor shaft sleeve, assembling internal threads are arranged at two ends of the motor shaft, the radial shaft sleeve is assembled on the fixed shaft sleeve through an inner hole, a locking ring groove is formed in the turbine rotor, and the locking ring is located in the locking ring groove of the turbine rotor and the compressor impeller. This rotor structure can show reinforcing rotor joint strength, improves the operating stability of closed circulation runoff turbine power generation system rotor, can prevent simultaneously that the rotor from taking place the pine and taking off in the course of the work, improves the operational reliability of rotor.
Description
Technical Field
The invention belongs to the field of structural design of a closed circulation radial flow type turbine power generation system, and particularly relates to a built-in locking gas floating rotor of the closed circulation turbine power generation system.
Background
As a novel efficient thermodynamic conversion form, the closed-cycle turbine power generation system can realize conversion from heat energy to electric energy through thermodynamic processes such as heat absorption, expansion work, heat release, compression and the like under a closed environment by means of certain gas work. A typical closed cycle radial flow turbine power generation system mainly comprises a turbine, a gas compressor, a generator, a heat regenerator and the like.
The rotor of the closed-cycle radial-flow turbine power generation system is one of the most core components in the closed-cycle radial-flow turbine power generation system, comprises a turbine, a gas compressor rotor and a generator rotor, and plays a decisive role in stable operation, thermoelectric conversion efficiency, reliability and service life of the system. In the operation process of the closed circulation radial flow turbine power generation system, the rotor is in a high-speed rotation state, the rotation speed of the rotor can reach tens of thousands of revolutions per minute, and some rotors even reach hundreds of thousands of revolutions per minute. Therefore, the reliability of the rotor is critical to the safe operation of the closed turbine power generation system.
The rotor of the existing closed circulation radial turbine power generation system mainly comprises a turbine rotor, a main shaft, a compressor impeller, a motor shaft, a coupler and other parts, and the turbine and the compressor impeller rotor are connected with the motor rotor through interference connection by means of the coupler, specifically comprising the following steps: the main shaft is respectively connected with a turbine rotor wheel back boss and a compressor impeller wheel back boss in an interference manner through inner holes at two ends of the main shaft to form a power rotating shaft, and then the power rotating shaft and the motor shaft are connected together through the interference assembly between the inner holes at two ends of the shaft coupling and a hub at one end of the motor shaft and the inlet end of the compressor impeller to form a complete rotor. Although the existing closed cycle turbine power generation system rotor structure can ensure the coaxiality of various parts of the rotor to a certain degree, the interference connection strength depends on the assembly size and the tolerance of the various parts, and high requirements are provided for the machining precision of the assembly parts of the parts; in addition, the rotor is influenced by the working load, the actual interference magnitude of the connecting part can be reduced, the connecting strength and rigidity of the rotor cannot be effectively guaranteed, the rotor component parts are easy to loosen, and the working reliability of the closed-cycle turbine power generation system is seriously influenced.
Aiming at the characteristics and the use requirements of a rotor and a bearing of a closed circulation radial flow turbine power generation system, the rotor structure is reasonably designed, and the manufacturing process of the rotor is optimized, so that the key for improving the operation stability of the closed circulation radial flow turbine power generation system and ensuring the reliability of the system is realized.
Disclosure of Invention
The invention provides a built-in locking gas floating rotor of a closed circulation turbine power generation system, aiming at the design problem of the rotor of the closed circulation radial flow turbine power generation system. According to the size parameters of a turbine impeller, a compressor impeller and a motor of the closed-cycle turbine power generation system, the structure sizes and the assembling and screwing moments of the compressor impeller, a locking ring, a composite shaft sleeve, a connecting bearing, a transition shaft sleeve, a motor shaft, a fixed shaft sleeve, a radial shaft sleeve and a turbine rotor are reasonably designed. On the basis of finishing the processing of the rotor structure component, firstly finishing the assembly of the turbine end radial shaft sleeve assembly and the motor shaft, secondly finishing the assembly of the turbine end radial shaft sleeve assembly, the motor shaft and the turbine rotor and the assembly of the transition shaft sleeve and the motor shaft, then finishing the assembly of the compressor end composite shaft sleeve assembly and the transition shaft sleeve, and finally finishing the assembly of the compressor impeller and the compressor end composite shaft sleeve assembly, the turbine rotor and the locking ring, thereby realizing the locking of the rotor structure. The rotor structure reduces the number of supporting points, can reduce the manufacturing difficulty of the rotor, can obviously improve the operation stability of the closed circulation radial flow turbine power generation system, and can prevent the rotor structure from loosening in the working process and improve the reliability of the rotor structure.
The technical scheme of the invention is as follows:
a built-in locking gas floating rotor of a closed circulation turbine power generation system comprises a gas compressor impeller, a locking ring, a composite shaft sleeve, a connecting bearing, a transition shaft sleeve, a motor shaft, a fixed shaft sleeve, a radial shaft sleeve and a turbine rotor. The center of the compressor impeller is provided with a threaded hole, and the rotating direction of the internal thread of the compressor impeller is opposite to the rotating direction of a rotor of the turbine power generation system during working; the center of the compressor impeller is provided with a threaded hole in which a locking ring groove is arranged, and the compressor impeller is provided with an outer cylindrical surface assembled with a connecting shaft sleeve; the composite shaft sleeve is provided with an annular end face matched with the axial thrust bearing, the composite shaft sleeve is made of a ceramic material with self-lubricating property, wear resistance and high temperature resistance, and the composite shaft sleeve is assembled on the connecting shaft sleeve through an inner hole; one end of the connecting shaft sleeve is provided with an inner cylindrical surface assembled with the compressor impeller, one end of the connecting shaft sleeve is provided with an outer cylindrical surface assembled with the composite shaft sleeve, and the other end of the connecting shaft sleeve is provided with an external thread assembled with the internal thread of the transition shaft sleeve; the inner side of the transition shaft sleeve is provided with an internal thread assembled with the external thread of the connecting shaft sleeve, and the outer side of the transition shaft sleeve is provided with an external thread assembled with the internal thread at one end of the motor shaft; the motor shaft consists of a magnetic core and a motor shaft sleeve, the magnetic core of the motor shaft is positioned in the motor shaft sleeve, one end of the motor shaft is provided with an internal thread assembled with the transition shaft sleeve, and the other end of the motor shaft is provided with an internal thread assembled with the external thread of the turbine rotor; the radial shaft sleeve is of a circular ring structure, is made of wear-resistant and high-temperature-resistant ceramic materials, and is assembled on the fixed shaft sleeve through an inner hole; the fixed shaft is sleeved with an internal thread assembled with the external thread of the turbine rotor, and the fixed shaft is sleeved with an external cylindrical surface assembled with the radial shaft sleeve; the turbine rotor is formed by welding a turbine impeller and a rotating shaft, an external thread assembled with an internal thread of a fixed shaft sleeve and an internal thread of a motor shaft is arranged on the turbine rotor, an external thread assembled with an internal thread hole of a compressor impeller is arranged on the turbine rotor, a locking ring groove is arranged on the turbine rotor, and a clamping nut is arranged at one end of the turbine rotor; the locking ring is positioned in the locking ring grooves of the turbine rotor and the compressor impeller.
A method for manufacturing a built-in locking gas floating rotor of a closed cycle turbine power generation system comprises the following steps:
a. determining the size parameters of a built-in locking gas floating rotor of a closed cycle turbine power generation system: according to the size parameters of a turbine, a gas compressor and a motor of the closed-cycle turbine power generation system, determining the structural sizes of rotor components of the turbine power generation system, namely a gas compressor impeller, a locking ring, a composite shaft sleeve, a connecting bearing, a transition shaft sleeve, a motor shaft, a fixed shaft sleeve, a radial shaft sleeve and a turbine rotor;
b. determining the assembly tightening torque of the rotor structure: according to the rotor dynamic characteristics and the torque transmission requirements of the closed cycle turbine power generation system, determining the tightening torque of the screw assembly of the parts consisting of the built-in locking gas floating rotor of the closed cycle turbine power generation system;
c. manufacturing the rotor structure component of the turbine power generation system: b, respectively processing a compressor impeller, a locking ring, a composite shaft sleeve, a connecting bearing, a transition shaft sleeve, a motor shaft, a fixed shaft sleeve, a radial shaft sleeve and a turbine rotor according to the size parameters of the components of the turbine power generation system rotor determined in the step a;
d. assembling a turbine end radial shaft sleeve assembly: and the radial shaft sleeve is assembled on the outer cylindrical surface of the fixed shaft sleeve in an interference fit mode to form a turbine end radial shaft sleeve assembly.
e. Assembling a motor shaft magnetic core and a motor shaft sleeve: c, heating the motor shaft sleeve to realize interference assembly of the motor shaft magnetic core and the motor shaft sleeve, so that one end of the motor shaft magnetic core is tightly attached to the inner end face of the shaft sleeve to form a complete motor shaft;
f. assembling the turbine end radial shaft sleeve assembly and the motor shaft between the turbine rotor: c, according to the screwing torque determined in the step b, screwing through threads, sequentially assembling the turbine end radial shaft sleeve assembly formed in the step d and the motor shaft formed in the step e on a turbine rotor, and ensuring that end faces are attached to each other;
g. assembling between the transition shaft sleeve and the motor shaft: b, according to the tightening torque determined in the step b, screwing through threads, and assembling the transition shaft sleeve on the motor shaft to enable the end face of the transition shaft sleeve to be tightly attached to the magnetic core of the motor shaft;
h. assembling a compressor end composite shaft sleeve assembly: and assembling the composite shaft sleeve on the outer cylindrical surface of the connecting shaft sleeve in an interference fit mode to form the composite shaft sleeve assembly at the compressor end.
i. Assembling the composite shaft sleeve component at the end of the compressor and the transition shaft sleeve: assembling the compressor end composite shaft sleeve assembly formed in the step h and the transition shaft sleeve together according to the screw assembling and screwing torque determined in the step b, and ensuring that the end surfaces are attached to each other;
j. assembling a compressor impeller and a compressor end composite shaft sleeve assembly, a turbine rotor and a locking ring: and c, mounting the locking ring on a turbine rotor locking ring groove, assembling the compressor impeller with the compressor end composite shaft sleeve assembly, the turbine rotor and the locking ring together by screwing the compressor impeller and the turbine rotor through threads according to the screwing torque determined in the step b, and ensuring that the locking ring is bounced into the compressor impeller locking ring groove to realize locking.
The invention has the beneficial effects that:
according to the built-in locking gas floating rotor of the closed type circulating turbine power generation system, the structure that the motor shaft, the turbine and the gas compressor rotating shaft are integrated is adopted, a coupler structure is avoided, the overall rigidity of the rotor can be improved, and the stability and the reliability of the operation of the rotor of the turbine power generation system are obviously enhanced; the composite shaft sleeve and the radial shaft sleeve are made of ceramic materials with self-lubricating property, wear resistance and high temperature resistance, so that the abrasion loss of a contact part of a gas floating bearing and a rotor in a closed cycle turbine power generation system during starting and stopping can be greatly reduced, and the service life of the turbine power generation system is prolonged; adopt locking structure, can prevent effectively that rotor structure from taking place the pine in the course of the work and taking off, further improve the operational reliability of rotor.
Drawings
FIG. 1 is a schematic view of a locked gas floating rotor built in a closed cycle turbine power generation system according to an embodiment of the present invention.
Fig. 2 is a partially enlarged schematic view of the locking structure according to the embodiment of the present invention.
Fig. 3 is a schematic structural diagram of a compressor wheel according to an embodiment of the present invention.
Fig. 4 is a schematic structural diagram of a composite bushing according to an embodiment of the present invention.
Fig. 5 is a schematic structural diagram of the connecting bushing according to the embodiment of the invention.
Fig. 6 is a schematic structural diagram of a transition bushing according to an embodiment of the present invention.
Fig. 7 is a schematic view of a motor shaft structure according to an embodiment of the present invention.
Fig. 8 is a schematic structural view of a fixed shaft sleeve according to an embodiment of the invention.
FIG. 9 is a schematic view of a turbine rotor according to an embodiment of the present invention.
1 compressor impeller 2 composite shaft sleeve 3 connecting shaft sleeve 4 transition shaft sleeve 5 motor shaft 6 radial shaft sleeve 7 fixed shaft sleeve 8 turbine rotor 9 locking ring 10 compressor impeller outer cylindrical surface 11 compressor impeller internal thread 12 compressor impeller locking ring groove 13 composite shaft sleeve annular end surface 14 composite shaft sleeve internal hole 15 connecting shaft sleeve inner cylindrical surface 16 connecting shaft sleeve outer cylindrical surface 17 connecting shaft sleeve external thread 18 transition shaft sleeve external thread 19 transition shaft sleeve internal thread 20 motor shaft sleeve 21 motor shaft magnetic core 22 motor shaft and turbine rotor external thread matched internal thread 23 motor shaft and transition shaft sleeve matched internal thread 24 fixed shaft sleeve outer cylindrical surface 25 fixed shaft sleeve internal thread 26 turbine rotor external thread 27 turbine rotor and compressor impeller assembly external thread 28 turbine rotor locking ring groove 29 turbine rotor clamping nut.
Detailed Description
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.
A built-in locking gas floating rotor of a closed circulation turbine power generation system comprises a compressor impeller 1, a locking ring 9, a composite shaft sleeve 2, a connecting bearing 3, a transition shaft sleeve 4, a motor shaft 5, a fixed shaft sleeve 7, a radial shaft sleeve 6 and a turbine rotor 8. The center of the compressor impeller 1 is provided with a threaded hole 11, the rotating direction of an internal thread of the compressor impeller 1 is opposite to the rotating direction of a rotor of a turbine power generation system when the rotor works, the center of the compressor impeller 1 is provided with a locking ring groove 12, and the compressor impeller 1 is provided with an outer cylindrical surface 10 assembled with a connecting shaft sleeve; the composite shaft sleeve 2 is provided with an annular end face 13 matched with an axial thrust bearing, the composite shaft sleeve 2 is made of a ceramic material with self-lubricating property, wear resistance and high temperature resistance, and the composite shaft sleeve 2 is assembled on the connecting shaft sleeve through an inner hole 14; one end of the connecting shaft sleeve 3 is provided with an inner cylindrical surface 15 assembled with the compressor impeller 1, one end of the connecting shaft sleeve 3 is provided with an outer cylindrical surface 16 assembled with the composite shaft sleeve, and the other end of the connecting shaft sleeve 3 is provided with an external thread 17 assembled with the internal thread of the transition shaft sleeve; the inner side of the transition shaft sleeve 4 is provided with an internal thread 19 assembled with the external thread of the connecting shaft sleeve, and the outer side of the transition shaft sleeve 4 is provided with an external thread 18 assembled with the internal thread at one end of the motor shaft; the motor shaft 5 consists of a magnetic core 21 and a motor shaft sleeve 20, the magnetic core 21 of the motor shaft 5 is positioned in the motor shaft sleeve 20, one end of the motor shaft 5 is provided with an internal thread 23 assembled with the transition shaft sleeve, and the other end of the motor shaft 5 is provided with an internal thread 22 assembled with the external thread of the turbine rotor; the radial shaft sleeve 6 is of a circular structure, the radial shaft sleeve 6 is made of a wear-resistant and high-temperature-resistant ceramic material, and the radial shaft sleeve 6 is assembled on the fixed shaft sleeve through an inner hole; the fixed shaft sleeve 7 is provided with an internal thread 25 assembled with the external thread of the turbine rotor, and the fixed shaft sleeve 7 is provided with an external cylindrical surface 24 assembled with the radial shaft sleeve; the turbine rotor 8 is formed by welding a turbine impeller and a rotating shaft, an external thread 26 assembled with an internal thread of a fixed shaft sleeve and an internal thread of a motor shaft is arranged on the turbine rotor 8, an external thread 27 assembled with an internal thread hole of a compressor impeller is arranged on the turbine rotor 8, a locking ring groove 28 is arranged on the turbine rotor 8, and a clamping nut 29 is arranged at one end of the turbine rotor 8; the locking ring 9 is located in the locking ring groove 12 of the turbine rotor and the locking ring groove 28 of the compressor wheel.
A method for manufacturing a built-in locking gas floating rotor of a closed cycle turbine power generation system comprises the following steps:
a. determining the size parameters of a built-in locking gas floating rotor of a closed cycle turbine power generation system: according to the size parameters of a turbine, a gas compressor and a motor of the closed-cycle turbine power generation system, determining the structural sizes of rotor components of the turbine power generation system, namely a gas compressor impeller 1, a locking ring 9, a composite shaft sleeve 2, a connecting bearing 3, a transition shaft sleeve 4, a motor shaft 5, a fixed shaft sleeve 7, a radial shaft sleeve 6 and a turbine rotor 8;
the diameter of a turbine impeller of a certain type of closed cycle turbine power generation system of the embodiment is phi 90mm, the diameter of a compressor impeller is phi 96mm, the diameter of a motor shaft is phi 38mm, the rotating direction of a rotor of the turbine power generation system in working is right-handed, the size of an internal thread 11 of the compressor impeller 1 is determined to be M12 multiplied by 1-H7H7-LH according to the size parameters of the turbine impeller, the compressor impeller and the motor of the closed cycle turbine power generation system, the diameter of an external cylindrical surface 10 of the compressor impeller 1 is phi 20mm, the diameter of an internal cylindrical surface 14 of the composite shaft sleeve 2 is phi 28mm, the size of a diameter of an internal cylindrical surface 15 of the connecting shaft sleeve 3 is phi 20mm, the size of an external cylindrical surface 16 is phi 28mm, the size of an external thread 17 is M24 multiplied by 1-p6p6-LH, the sizes of an internal thread 19 and an external thread 18 of the transition shaft sleeve 4 are respectively M24 multiplied by 1-H7H7-LH and M36 multiplied by 1-p6p6-LH, the inner hole diameter of the magnetic core 21 of the motor shaft 5 is determined to be phi 14mm, the size of the internal thread 23 is M36 multiplied by 1-H7H7-LH, the size of the internal thread 22 is M20 multiplied by 1-H7H7-LH, the inner diameter and the outer diameter of the determined radial shaft sleeve 6 are phi 28mm and phi 36mm respectively, the size of the internal thread 25 of the determined fixed shaft sleeve 7 is M24 multiplied by 1-H7H7-LH, the size of the external thread 27 of the determined turbine rotor 8 is M12 multiplied by 1-p6p6-LH, and the size of the external thread 26 is M24 multiplied by 1-p6p 6-LH.
b. Determining the assembly tightening torque of the rotor structure: according to the rotor dynamics characteristic and the torque transmission requirement of the closed cycle turbine power generation system, determining the tightening torque of the screw assembly of the part consisting of the built-in locking gas floating rotor of the closed cycle turbine power generation system;
c. manufacturing the rotor structure component of the turbine power generation system: b, respectively processing a compressor impeller, a locking ring, a composite shaft sleeve, a connecting bearing, a transition shaft sleeve, a motor shaft, a fixed shaft sleeve, a radial shaft sleeve and a turbine rotor according to the size parameters of the components of the turbine power generation system rotor determined in the step a;
d. assembling a turbine end radial shaft sleeve assembly: assembling the radial shaft sleeve on the outer cylindrical surface of the fixed shaft sleeve in an interference fit mode to form a turbine end radial shaft sleeve assembly;
e. assembling a motor shaft magnetic core and a motor shaft sleeve: c, heating the motor shaft sleeve to realize interference assembly of the motor shaft magnetic core and the motor shaft sleeve, so that one end of the motor shaft magnetic core is tightly attached to the inner end face of the shaft sleeve to form a complete motor shaft;
f. assembling the turbine end radial shaft sleeve assembly and the motor shaft between the turbine rotor: c, according to the screwing torque determined in the step b, screwing through threads, sequentially assembling the turbine end radial shaft sleeve assembly formed in the step d and the motor shaft formed in the step e on a turbine rotor, and ensuring that end faces are attached to each other;
g. assembling between the transition shaft sleeve and the motor shaft: b, according to the tightening torque determined in the step b, screwing through threads, and assembling the transition shaft sleeve on the motor shaft to enable the end face of the transition shaft sleeve to be tightly attached to the magnetic core of the motor shaft;
h. assembling a compressor end composite shaft sleeve assembly: assembling the composite shaft sleeve on the outer cylindrical surface of the connecting shaft sleeve in an interference fit mode to form a compressor end composite shaft sleeve assembly;
i. assembling the composite shaft sleeve component at the end of the compressor and the transition shaft sleeve: assembling the compressor end composite shaft sleeve assembly formed in the step h and the transition shaft sleeve together according to the screw assembling and screwing torque determined in the step b, and ensuring that the end surfaces are attached to each other;
j. assembling the compressor impeller and the compressor end composite shaft sleeve assembly, the turbine rotor and the locking ring: and c, mounting the locking ring on a turbine rotor locking ring groove, assembling the compressor impeller with the compressor end composite shaft sleeve assembly, the turbine rotor and the locking ring together by screwing the compressor impeller and the turbine rotor through threads according to the screwing torque determined in the step b, and ensuring that the locking ring is bounced into the compressor impeller locking ring groove to realize locking.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (6)
1. The utility model provides a built-in locking gas floating rotor of closed circulation turbine power generation system which characterized in that: the compressor impeller comprises a compressor impeller (1), a locking ring (9), a composite shaft sleeve (2), a connecting shaft sleeve (3), a transition shaft sleeve (4), a motor shaft (5), a fixed shaft sleeve (7), a radial shaft sleeve (6) and a turbine rotor (8);
a threaded hole (11) is formed in the center of the compressor impeller (1), the rotating direction of an internal thread of the compressor impeller (1) is opposite to the rotating direction of a rotor of a turbine power generation system when the rotor works, a first locking ring groove (12) is formed in the threaded hole in the center of the compressor impeller (1), and an outer cylindrical surface (10) assembled with a connecting shaft sleeve is arranged on the compressor impeller (1);
the composite shaft sleeve (2) is provided with an annular end face (13) matched with an axial thrust bearing, the composite shaft sleeve (2) is made of a ceramic material with self-lubrication, wear resistance and high temperature resistance, and the composite shaft sleeve (2) is assembled on the connecting shaft sleeve through an inner hole (14);
one end of the connecting shaft sleeve (3) is provided with an inner cylindrical surface (15) assembled with the compressor impeller (1), one end of the connecting shaft sleeve (3) is provided with an outer cylindrical surface (16) assembled with the composite shaft sleeve, and the other end of the connecting shaft sleeve (3) is provided with an external thread (17) assembled with the internal thread of the transition shaft sleeve;
the inner side of the transition shaft sleeve (4) is provided with an internal thread (19) assembled with the external thread of the connecting shaft sleeve, and the outer side of the transition shaft sleeve (4) is provided with an external thread (18) assembled with the internal thread at one end of the motor shaft;
the motor shaft (5) consists of a magnetic core (21) and a motor shaft sleeve (20), the magnetic core (21) of the motor shaft (5) is positioned inside the motor shaft sleeve (20), one end of the motor shaft (5) is provided with an internal thread (23) assembled with the transition shaft sleeve, and the other end of the motor shaft (5) is provided with an internal thread (22) assembled with the external thread of the turbine rotor;
the radial shaft sleeve (6) is of a circular structure, the radial shaft sleeve (6) is made of wear-resistant and high-temperature-resistant ceramic materials, and the radial shaft sleeve (6) is assembled on the fixed shaft sleeve through an inner hole;
the fixed shaft sleeve (7) is provided with an internal thread (25) assembled with the external thread of the turbine rotor, and the fixed shaft sleeve (7) is provided with an external cylindrical surface (24) assembled with the radial shaft sleeve;
the turbine rotor (8) is formed by welding a turbine impeller and a rotating shaft, an external thread (26) assembled with an internal thread of a fixed shaft sleeve and an internal thread of a motor shaft is arranged on the turbine rotor (8), an external thread (27) assembled with an internal thread hole of a compressor impeller is arranged on the turbine rotor (8), a second locking ring groove (28) is arranged on the turbine rotor (8), and a clamping nut (29) is arranged at one end of the turbine rotor (8);
the locking ring (9) is positioned in a second locking ring groove (28) of the turbine rotor and a first locking ring groove (12) of the compressor impeller.
2. The method of manufacturing a closed cycle turbine power generation system internal lock gas floating rotor of claim 1, wherein: the method comprises the following steps:
a. determining the size parameter of a built-in locking gas floating rotor of a closed cycle turbine power generation system;
b. determining the assembling and screwing torque of the rotor structure;
c. manufacturing the rotor structure component of the turbine power generation system;
d. assembling a turbine end radial shaft sleeve assembly: assembling the radial shaft sleeve on the outer cylindrical surface of the fixed shaft sleeve in an interference fit mode to form a turbine end radial shaft sleeve assembly;
e. assembling a motor shaft magnetic core and a motor shaft sleeve;
f. assembling the turbine end radial shaft sleeve assembly, the motor shaft and the turbine rotor;
g. assembling the transition shaft sleeve and the motor shaft;
h. assembling a composite shaft sleeve assembly at the end of a compressor;
i. assembling the composite shaft sleeve component at the end of the compressor and the transition shaft sleeve: assembling the compressor end composite shaft sleeve assembly formed in the step h and the transition shaft sleeve together according to the screw assembling and screwing torque determined in the step b, and ensuring that the end surfaces are attached to each other;
j. and assembling the compressor impeller with a compressor end composite shaft sleeve assembly, a turbine rotor and a locking ring.
3. The method of manufacturing a closed cycle turbine power generation system built-in lock gas floating rotor according to claim 2, wherein: and f, according to the screwing torque determined in the step b, screwing through threads, sequentially assembling the radial shaft sleeve assembly at the turbine end formed in the step d and the motor shaft formed in the step e on a turbine rotor, and ensuring that the end surfaces are attached to each other.
4. The method of manufacturing a closed cycle turbine power generation system built-in lock gas floating rotor according to claim 2, wherein: in step g: and c, screwing through the threads according to the screwing torque determined in the step b, and assembling the transition shaft sleeve on the motor shaft to enable the end face of the transition shaft sleeve to be tightly attached to the magnetic core of the motor shaft.
5. The method of manufacturing a closed cycle turbine power generation system built-in lock gas floating rotor according to claim 2, wherein: in step h: and assembling the composite shaft sleeve on the outer cylindrical surface of the connecting shaft sleeve in an interference fit mode to form the composite shaft sleeve assembly at the compressor end.
6. The method of manufacturing a closed cycle turbine power generation system built-in lock gas floating rotor according to claim 2, wherein: in step j: and c, installing a locking ring on a turbine rotor locking ring groove, assembling the compressor impeller with the compressor end composite shaft sleeve assembly, the turbine rotor and the locking ring together through screwing and assembling the compressor impeller with the turbine rotor through threads according to the screwing torque determined in the step b, and ensuring that the locking ring is bounced into the compressor impeller locking ring groove to realize locking.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910647952.5A CN110332019B (en) | 2019-07-18 | 2019-07-18 | Built-in locking gas floating rotor of closed circulation turbine power generation system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910647952.5A CN110332019B (en) | 2019-07-18 | 2019-07-18 | Built-in locking gas floating rotor of closed circulation turbine power generation system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110332019A CN110332019A (en) | 2019-10-15 |
| CN110332019B true CN110332019B (en) | 2022-07-05 |
Family
ID=68145775
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910647952.5A Active CN110332019B (en) | 2019-07-18 | 2019-07-18 | Built-in locking gas floating rotor of closed circulation turbine power generation system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110332019B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11434918B2 (en) * | 2019-06-21 | 2022-09-06 | Danfoss A/S | Partially hollow shaft for HVAC compressor |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10002092A1 (en) * | 1999-12-07 | 2001-06-13 | Loher Ag | Electric drive e.g. for ship propeller, has inside rotor connected with first impeller and outer rotor concentric with it connected with second impeller |
| JP2010119264A (en) * | 2008-11-14 | 2010-05-27 | Ngk Insulators Ltd | Rotor for compact gas turbine generator |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7112036B2 (en) * | 2003-10-28 | 2006-09-26 | Capstone Turbine Corporation | Rotor and bearing system for a turbomachine |
| CN102102546A (en) * | 2009-12-18 | 2011-06-22 | 北京智慧剑科技发展有限责任公司 | Impeller generator and method for generating power |
| US9664050B2 (en) * | 2013-10-25 | 2017-05-30 | Ecomotors, Inc. | Bearings for a turbomachine having an electric motor |
| CN105927294B (en) * | 2016-05-18 | 2018-05-15 | 中国北方发动机研究所(天津) | Exhaust turbine generation device |
| CN106988784A (en) * | 2017-03-24 | 2017-07-28 | 中国北方发动机研究所(天津) | A kind of radial-flow type rotating shaft of supercharger turbine structure and its moulding process |
| CN107091156B (en) * | 2017-06-30 | 2018-12-28 | 西安中工动力能源有限公司 | A kind of micro-gas-turbine machine rotor and assembly method |
| CN108643979B (en) * | 2018-04-10 | 2020-11-06 | 中国北方发动机研究所(天津) | Supercritical carbon dioxide closed cycle turbo compressor |
-
2019
- 2019-07-18 CN CN201910647952.5A patent/CN110332019B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10002092A1 (en) * | 1999-12-07 | 2001-06-13 | Loher Ag | Electric drive e.g. for ship propeller, has inside rotor connected with first impeller and outer rotor concentric with it connected with second impeller |
| JP2010119264A (en) * | 2008-11-14 | 2010-05-27 | Ngk Insulators Ltd | Rotor for compact gas turbine generator |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110332019A (en) | 2019-10-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110344890B (en) | High-reliability turbine power generation system rotor structure and manufacturing process | |
| CN110332018B (en) | High-compactness closed circulation runoff turbine power generation system rotor | |
| CN110318815B (en) | Ceramic rotor of closed-cycle turbine power generation system | |
| CN110360148B (en) | Threaded connection rotor structure of turbine thermoelectric conversion system | |
| CN110344892B (en) | Radial flow turbine power generation system integrated rotor and manufacturing process thereof | |
| CN110332020B (en) | Closed circulation turbine power generation system rotor structure based on air bearing | |
| CN110332019B (en) | Built-in locking gas floating rotor of closed circulation turbine power generation system | |
| CN110374691B (en) | Radial flow turbine power generation system gas lubrication rotor structure | |
| CN110344891B (en) | Rotor structure and process of long-life closed circulation turbine power generation system | |
| CN110318812B (en) | Gas lubrication ceramic rotor of radial flow turbine power generation system and manufacturing method thereof | |
| CN110374692B (en) | Integrated rotor structure of radial turbine power generation system | |
| CN110374693B (en) | Detachable radial flow turbine power generation system rotor structure and process | |
| CN112360577B (en) | Rotor structure and process of combined impeller power generation system | |
| CN110374684B (en) | Closed circulation turbine power generation system rotor based on electromagnetic bearing | |
| CN112360574B (en) | Rotating assembly structure of high-speed low-stress turbine power generation system | |
| CN110318813B (en) | Magnetic suspension rotor structure of closed circulation radial flow turbine power generation system | |
| CN110318814B (en) | Closed-cycle turbine power generation system component test rotor and manufacturing method thereof | |
| CN209959668U (en) | Bolt for connecting gas compressor rotor and turbine shaft of gas turbine | |
| CN112360565A (en) | Twin dissimilar material composite runoff impeller and manufacturing process thereof | |
| CN112350507B (en) | High-power-density closed-cycle thermoelectric conversion system rotor | |
| CN112360573B (en) | Rotating assembly of compact radial-flow turbine thermoelectric conversion system | |
| CN217735581U (en) | Multistage impeller rotor structure and generating set | |
| CN112360570B (en) | Runoff impeller side-mounted high-speed thermoelectric conversion system rotating shaft and process thereof | |
| CN103362557A (en) | Inserting pin tightening shaft type impeller and connecting structure of impeller and turbine shaft | |
| CN117703531A (en) | High-speed ceramic turbine rotor and manufacturing method thereof |
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 |