CN209742980U - Cooling device for rotor supporting structure of gas turbine - Google Patents

Abstract

The utility model relates to a gas turbine rotor supporting structure cooling device, which comprises a rotating shaft, be equipped with the multistage blade of compressor and turbine blade in the pivot respectively, the left end of the multistage blade of compressor is equipped with first radial magnetic bearing, first radial magnetic bearing left side is equipped with thrust bearing, the right-hand member of the multistage blade of compressor is equipped with the radial magnetic bearing of second, the outside of the radial magnetic bearing of second is equipped with the bearing frame, the outside of first radial magnetic bearing is equipped with the heat conduction seat, the upper portion of heat conduction seat is equipped with the condensation seat, be equipped with the cooler in the condensation seat, the lower part of heat conduction seat is equipped with the casing, be equipped with the pipe on the casing, pipe one end communicates with the rear portion. The utility model discloses a can derive the heat of bearing and carry out the dispersion heat dissipation, simultaneously, the cold air that produces in the condensation seat can cool down first radial magnetic bearing and the radial magnetic bearing of second. The device has the advantages of compact structure, good cooling effect, high reliability and low operation cost.

Description

Cooling device for rotor supporting structure of gas turbine

Technical Field

The utility model belongs to the technical field of small-size gas turbine, in particular to gas turbine rotor supporting structure cooling device.

background

The choice of gas turbine support scheme and support bearing type is related to engine structure, mass, and performance. Are factors that play a critical role in engine efficiency, performance retention and service life, and also affect the rotor dynamics of the rotor, and must be carefully considered in the design of the structural solution.

At present, ball bearings, sliding bearings and oil film bearings are mainly adopted by the domestic gas turbine, the bearings are in mechanical contact, high temperature is generated in the high-speed operation process, a lubricating system is needed, the operating and maintaining cost is increased by the factors, and the service life of the gas turbine is influenced. Compared with the bearings, the stator and the rotor of the magnetic bearing have no mechanical wear, the combustion engine does not need to be provided with a lubricating system, the rotor can run to a higher rotating speed, but the temperature of the magnetic bearing can be gradually increased along with the long-term running of the rotor, the accumulated temperature has certain damage to the magnetic bearing, the energy consumption is increased, the noise is increased, the service life is shortened due to the long-term running at a high temperature, the precision of the magnetic bearing can be influenced due to the change of the temperature, the operating cost of the combustion engine is greatly increased, and the service life of each running element is shortened.

SUMMERY OF THE UTILITY MODEL

The invention provides a cooling device for a rotor supporting structure of a gas turbine, which aims to solve the technical problem of operation cooling of the magnetic bearings.

The utility model provides a technical scheme that above-mentioned technical problem took is: the cooling device for the rotor supporting structure of the gas turbine is structurally characterized by comprising a rotating shaft, wherein a compressor multistage blade and a turbine blade are arranged on the rotating shaft respectively, the compressor multistage blade and the turbine blade are connected with the rotating shaft and rotate synchronously with the rotating shaft, a first radial magnetic bearing is arranged at the left end of the compressor multistage blade, a thrust bearing is arranged at the left side of the first radial magnetic bearing, a second radial magnetic bearing is arranged at the right end of the compressor multistage blade, a bearing seat is arranged outside the second radial magnetic bearing, a heat conducting seat is arranged on the outer side of the first radial magnetic bearing, a condensing seat is arranged on the upper portion of the heat conducting seat, a cooler is arranged in the condensing seat, a shell is arranged at the lower portion of the heat conducting seat, a guide pipe is arranged on the shell, one.

Further, the heat conducting seat and the bearing seat are respectively welded with the shell.

Furthermore, the interior of the heat conducting seat and the interior of the condensation seat are both semicircular, and the heat conducting seat is connected with the condensation seat through a bolt to form a complete circle and clamp the first radial magnetic bearing.

Further, the first radial magnetic bearing and the second radial magnetic bearing support the rotating shaft in the radial direction, and the thrust bearing supports the rotating shaft in the axial direction.

Further, the duct blows the low-temperature air generated by the cooler toward the second radial magnetic bearing.

Furthermore, a refrigeration host is arranged outside the condensation seat.

Furthermore, the heat conducting seat and the bearing seat are made of copper alloy or aluminum alloy with good heat conductivity.

The utility model has the advantages that: the utility model discloses a heat conduction seat and bearing frame can derive the casing with the heat of the radial magnetic bearing of first radial magnetic bearing and second and disperse the heat dissipation, and simultaneously, the cold air that produces in the condensation seat can cool down first radial magnetic bearing, and the pipe also can be defeated the cold air that produces in the condensation seat for the radial magnetic bearing of second to cool down it. The device has the advantages of compact structure, good cooling effect, high reliability and low operation cost.

Drawings

Fig. 1 is a schematic front view of the present invention;

FIG. 2 is a schematic structural diagram of a condensation seat of the present invention;

FIG. 3 is a schematic view of the structure of the cooler of the present invention;

Fig. 4 is a block diagram of the refrigeration main unit of the present invention;

In the figure: the compressor comprises a rotating shaft 1, compressor multistage blades 11, turbine blades 12, a first radial magnetic bearing 2, a thrust bearing 3, a second radial magnetic bearing 4, a bearing seat 5, a heat conducting seat 6, a condensation seat 7, a cooler 71, a refrigeration host 72, a compressor 721, a condenser 722, an expansion valve 723, a shell 8 and a guide pipe 9.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. The components of the embodiments of the present invention, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present invention, presented in the accompanying drawings, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. Based on the embodiment of the present invention, all other embodiments obtained by the person skilled in the art without creative work belong to the protection scope of the present invention.

As an example, as shown in fig. 1, fig. 2, fig. 3 and fig. 4, a cooling device for a rotor supporting structure of a gas turbine includes a rotating shaft 1, a compressor multistage blade 11 and a turbine blade 12 may be respectively disposed on the rotating shaft 1, the compressor multistage blade 11 and the turbine blade 12 may be connected to the rotating shaft 1 and may rotate synchronously with the rotating shaft 1, a first radial magnetic bearing 2, a thrust bearing 3 and a second radial magnetic bearing 4 may be respectively disposed at left and right ends of the compressor multistage blade 11, the first radial magnetic bearing 2 and the second radial magnetic bearing 4 may support a radial direction of the rotating shaft 1, the thrust bearing 3 may support an axial direction of the rotating shaft 1, the rotating shaft 1 operates to drive the compressor multistage blade 11 and the turbine blade 12 to generate a directional air flow, the air flow flows from an end of the compressor multistage blade 11 to an end of the turbine blade 12 and is discharged, and the cooling device is structurally characterized in that a bearing seat 5 may be disposed outside, the outer side of the first radial magnetic bearing 2 can be provided with a heat conducting seat 6, the heat conducting seat 6 and the bearing seat 5 can be made of copper alloy or aluminum alloy and other materials with good heat conductivity, the lower part of the heat conducting seat 6 can be provided with a shell 8, the heat conducting seat 6 and the bearing seat 5 can be respectively welded with the shell 8, so that partial heat generated by the first radial magnetic bearing 2 and the second radial magnetic bearing 4 can be dispersed along with air flow, and the heat can be transferred to the shell 8 through the heat conducting seat 6 and the bearing seat 5 to increase the heat dissipation area for cooling; the thrust bearing 3 only bears the axial part of the rotating shaft 1, the bearing load is extremely small, and the air flow generated by the multistage blades 11 and the turbine blades 12 of the air compressor can cool the multistage blades.

As an example, as shown in fig. 1, 2, 3 and 4, a condensation seat 7 may be disposed on an upper portion of a heat conduction seat 6, the interiors of the heat conduction seat 6 and the condensation seat 7 may be both semicircular, a full circle formed by the heat conduction seat 6 and the condensation seat 7 after being connected by bolts may clamp the first radial magnetic bearing 2, a cooler 71 may be disposed in the condensation seat 7, the two coolers 71 are symmetrically disposed in the condensation seat 7, a refrigeration host 72 may be disposed outside the condensation seat 7, the refrigeration host 72 is composed of a compressor 721, a condenser 722 and an expansion valve 723, the compressor 721, the condenser 722, the expansion valve 723 and the cooler 71 are connected in a closed loop manner by pipelines, refrigerant meson in the refrigeration host 72 is driven by the compressor 721, the meson releases heat and absorbs cold at the condenser 722, the meson releases cold at the end, the meson passes through the expansion valve 723 and then releases cold and absorbs heat at the two coolers 71 end connected in series, that is, i.e., low-temperature air, the high-temperature air is generated at the external refrigerating main machine 72 end of the condensation seat 7, and the high-temperature air generated by the external refrigerating main machine 72 can play a micro preheating role on the airflow generated by the compressor multistage blades 11, so that the efficiency of the gas engine is promoted. In addition, a conduit 9 can be arranged on the shell 8, one end of the conduit 9 can be communicated with the rear part of the condensation seat 7, the other end of the conduit 9 can be arranged at the front part of the bearing seat 5, and the conduit 9 can drive low-temperature air generated by the cooler 71 to blow to the front end of the second radial magnetic bearing 4 through air pressure generated by the rotation of the compressor multistage blades 11 and the turbine blades 12 so as to cool the second radial magnetic bearing 4, so that the efficient and stable operation of the second radial magnetic bearing 4 is ensured.

The utility model discloses a heat conduction seat 6 and bearing frame 5 can derive the heat of first radial magnetic bearing 2 and the radial magnetic bearing 4 of second and carry out the dispersion heat dissipation on the casing 8, and simultaneously, the cold air that produces in the condensation seat 7 can cool down first radial magnetic bearing 2, and pipe 9 also can be defeated the cold air that produces in the condensation seat 7 and cool down to it for the radial magnetic bearing 4 of second. The device has the advantages of compact structure, good cooling effect, high reliability and low operation cost.

The above description is only for the specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can easily think of the changes or substitutions within the technical scope of the present invention, and all should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be dominated by the protection scope of the claims.

Claims (7)

1. A gas turbine rotor support structure cooling apparatus characterized by: the device comprises a rotating shaft, wherein a compressor multistage blade and a turbine blade are arranged on the rotating shaft respectively, the compressor multistage blade and the turbine blade are connected with the rotating shaft and rotate synchronously with the rotating shaft, a first radial magnetic bearing is arranged at the left end of the compressor multistage blade, a thrust bearing is arranged on the left side of the first radial magnetic bearing, a second radial magnetic bearing is arranged at the right end of the compressor multistage blade, a bearing seat is arranged outside the second radial magnetic bearing, a heat conducting seat is arranged on the outer side of the first radial magnetic bearing, a condensing seat is arranged on the upper portion of the heat conducting seat, a cooler is arranged in the condensing seat, a shell is arranged on the lower portion of the heat conducting seat, a guide pipe is arranged on the shell.

2. A gas turbine rotor support structure cooling arrangement as claimed in claim 1, wherein: the heat conducting seat and the bearing seat are respectively welded with the shell.

3. A gas turbine rotor support structure cooling arrangement as claimed in claim 1, wherein: the interior of the heat conducting seat and the interior of the condensation seat are both semicircular, and the heat conducting seat is connected with the condensation seat through bolts to form a complete circle and clamp the first radial magnetic bearing.

4. A gas turbine rotor support structure cooling arrangement as claimed in claim 1, wherein: the first radial magnetic bearing and the second radial magnetic bearing support the rotating shaft in the radial direction, and the thrust bearing supports the rotating shaft in the axial direction.

5. A gas turbine rotor support structure cooling arrangement as claimed in claim 1, wherein: the duct blows the low-temperature air generated by the cooler toward the second radial magnetic bearing.

6. A gas turbine rotor support structure cooling arrangement as claimed in claim 1, wherein: and a refrigeration host is arranged outside the condensation seat.

7. a gas turbine rotor support structure cooling arrangement as claimed in claim 1, wherein: the heat conducting seat and the bearing seat are made of copper alloy or aluminum alloy with good heat conductivity.