CN117365661A - Forward and reverse rotation turbine and control method thereof - Google Patents
Forward and reverse rotation turbine and control method thereof Download PDFInfo
- Publication number
- CN117365661A CN117365661A CN202311610620.2A CN202311610620A CN117365661A CN 117365661 A CN117365661 A CN 117365661A CN 202311610620 A CN202311610620 A CN 202311610620A CN 117365661 A CN117365661 A CN 117365661A
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- Prior art keywords
- turbine
- reverse
- corotation
- rotation
- reverse rotation
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- 238000000034 method Methods 0.000 title claims abstract description 13
- 239000000498 cooling water Substances 0.000 claims description 3
- 238000005260 corrosion Methods 0.000 description 2
- 230000007797 corrosion Effects 0.000 description 2
- 238000000576 coating method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
Classifications
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- 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
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/30—Non-positive-displacement machines or engines, e.g. steam turbines characterised by having a single rotor operable in either direction of rotation, e.g. by reversing of blades
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- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
-
- 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
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
-
- 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
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
-
- 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
- F01D5/021—Blade-carrying members, e.g. rotors for flow machines or engines with only one axial stage
-
- 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
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Supercharger (AREA)
Abstract
The invention relates to the technical field of turbines, in particular to a forward and reverse turbine and a control method thereof, wherein the forward and reverse turbine comprises a forward turbine gas exhaust shell, a forward and reverse radial bearing, a forward and reverse thrust bearing, a nozzle cover, a forward turbine gas inlet shell, a forward turbine gas inlet control valve, a reverse turbine gas exhaust control valve, forward turbine blades, a reverse turbine blade disc and an adjustable flow area nozzle ring, the forward and reverse radial bearing is arranged on a radial forward and reverse bearing seat of the forward turbine gas exhaust shell, the forward and reverse thrust bearing is arranged on an axial forward and reverse bearing seat of the forward turbine gas exhaust shell, and the reverse turbine blade disc is arranged on a turbine shaft, and the forward and reverse turbine blades are arranged on the reverse turbine blade disc.
Description
Technical Field
The invention relates to the technical field of turbines, in particular to a forward and reverse rotation turbine and a control method thereof.
Background
At present, the traditional turbine structure such as a turbocharger, a turbine and the like can not realize the coaxial forward and reverse rotation function, and the two shafts or the angle of the movable vanes is changed to realize the forward and reverse rotation, so that the problems of high technical difficulty, low reliability and the like exist.
Disclosure of Invention
The invention aims to provide a forward and reverse rotation turbine and a control method thereof, and aims to solve the technical problems that in the prior art, the turbine structure such as a turbocharger, a turbine and the like cannot realize the coaxial forward and reverse rotation function, both adopt two shafts or change the angles of movable vanes to realize the forward and reverse rotation, and have larger technical difficulty and low reliability.
In order to achieve the above purpose, the invention adopts a forward and reverse turbine, which comprises a forward and reverse turbine gas exhaust shell, a forward and reverse radial bearing, a forward and reverse thrust bearing, a nozzle cover, a forward and reverse turbine gas inlet shell, a forward and reverse turbine gas inlet control valve, a reverse turbine exhaust control valve, forward and reverse turbine blades, a reverse turbine blade disc and an adjustable flow area nozzle ring, wherein the nozzle cover is arranged on the forward and reverse turbine gas exhaust shell, the forward and reverse turbine gas inlet shell is arranged on the forward and reverse turbine gas exhaust shell, the adjustable flow area nozzle ring is arranged on the forward and reverse turbine gas inlet shell, the forward and reverse turbine gas inlet control valve is also arranged on the forward and reverse turbine gas inlet shell, the forward and reverse radial bearing is arranged on a radial forward and reverse rotary bearing seat of the forward and reverse turbine gas exhaust shell, the forward and reverse turbine blade disc is arranged on an axial forward and reverse rotary bearing seat of the forward and reverse turbine blade disc is arranged on the forward and reverse turbine blade disc.
The turbine blade disc is provided with a mortise, and the turbine blade is provided with a tenon tooth part, and the tenon tooth part is arranged in the mortise.
Wherein the counter-rotating turbine blade disk comprises counter-rotating turbine blades disposed on a turbine shaft and a support ring disposed on the counter-rotating turbine blades.
The nozzle cover is designed into an expanding flow channel, the inner ring of the nozzle cover is matched with the blades of the forward turbine, and the outer ring of the nozzle cover is matched with the air inlet shell of the reverse turbine.
The reversing turbine blade is integrally milled by a turbine disc, and the root of the reversing turbine blade is designed with a special fillet so as to reduce stress concentration.
The forward and reverse rotation radial bearing and the forward and reverse rotation thrust bearing are both arranged to be oil wedge surfaces, and the forward and reverse rotation radial bearing and the oil wedge surfaces of the forward and reverse rotation thrust bearing are both designed to be symmetrical structures, namely, the forward rotation and the reverse rotation of the turbine shaft can both realize the function of supporting the rotor and providing thrust.
Wherein, there is the interference between adjustable flow area nozzle ring and the nozzle housing.
The invention also provides a method for controlling the forward and backward rotation turbine, which is used for controlling the forward and backward rotation turbine, and comprises the following steps:
step one: firstly, starting the forward and reverse rotation turbine to start working, wherein the initial rotation is forward rotation when the forward and reverse rotation turbine is started;
step two: automatically judging the working state of the forward and reverse rotation turbine through a control program;
step three: if the positive and negative rotation turbine needs to be reversed, the control mechanism automatically opens the exhaust control valve of the reverse rotation turbine and closes the gas inlet control valve of the positive rotation turbine, so that the positive and negative rotation turbine is quickly changed into reverse rotation from positive rotation.
In the third step, the control mechanism is a driving motor, the driving motor can cool the temperature of the driving motor through cooling water, and the reliability of the driving motor is improved.
The invention relates to a forward and backward turbine and a control method thereof, wherein a gas inlet shell of the forward turbine is designed into a rotary structure, an outer cavity is a gas inlet runner of the forward turbine, an inner cavity is a gas outlet runner of the backward turbine, the design is ingenious, the same shell can realize the gas inlet of the forward turbine and the gas outlet of the backward turbine, the number of the shells is reduced, the reliability of the turbine structure is improved, the backward turbine blades are integrally milled by a turbine disc, the number and the blade shape of the backward turbine blades are specially designed, the root parts of the backward turbine blades are provided with special round corners for reducing the stress concentration of the root parts of the backward turbine blades, the pneumatic efficiency and the structural strength of the backward turbine blades are simultaneously considered during the design, the rotational inertia of a rotor is simultaneously reduced, the gas inlet shell of the forward turbine is a reverse turbine exhaust shell, the forward turbine starts to work, the forward turbine starts to turn to forward when started, the working state of the forward turbine is automatically judged through a control program, if the forward turbine is detected to need to turn, a control mechanism automatically opens a reverse turbine exhaust control valve and closes a forward turbine gas inlet control valve, so that the forward turbine is quickly turned from forward to reverse, the reverse turbine exhaust control valve and the forward turbine gas inlet control valve are both arranged on the forward turbine gas inlet shell, the reverse turbine exhaust control valve and the forward turbine gas inlet control valve are linked, namely, when the turbine rotates forward, the forward turbine gas inlet control valve is opened, the reverse turbine gas exhaust control valve is closed, the high-temperature gas flows through the nozzle ring with adjustable flow area through the inlet flow passage of the inlet casing of the forward rotating turbine gas, blows the turbine to do work, and the turbine rotates forward, because the exhaust control valve of the reverse turbine, the turbine gas can not leak from the exhaust flow passage of the reverse turbine, when the turbine rotates reversely, the exhaust control valve of the reverse turbine is opened, the inlet control valve of the forward rotating turbine gas is closed, the air flow enters from the inlet flow passage of the reverse turbine, and directly blows the reverse turbine, so that the turbine shaft rotates reversely, and in this way, the problems that the traditional turbine structure such as a turbocharger, a turbine and the like can not realize the coaxial forward and reverse rotation function, and the forward and reverse rotation can be realized by adopting two shafts or changing the angle of a movable blade are solved, and the technical problems of great technical difficulty and low reliability exist.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of a forward and reverse turbine according to the present invention.
Fig. 2 is a schematic structural view of the reversing turbine blade tray of the present invention.
Fig. 3 is a schematic view of the structure of the present invention when the reverse rotation turbine blade disk is rotated forward.
Fig. 4 is a schematic view of the structure of the reversing turbine blade disc of the present invention in reversing.
FIG. 5 is a schematic view of the direction of flow of turbine gas during forward and reverse rotation of the turbine according to the present invention.
FIG. 6 is a schematic view of the direction of flow of turbine gas when the counter-rotating turbine of the present invention is reversed.
Fig. 7 is a schematic structural view of a forward turbine gas inlet casing of the present invention.
FIG. 8 is a flow chart of the steps of the method for controlling a forward and reverse turbine according to the present invention.
1-forward turbine gas exhaust casing, 2-forward and reverse radial bearing, 3-forward and reverse thrust bearing, 4-nozzle cover, 5-forward turbine gas inlet casing, 6-forward turbine gas inlet control valve, 7-reverse turbine exhaust control valve, 8-forward turbine blade, 9-reverse turbine blade disk, 10-adjustable flow area nozzle ring, 11-tongue-and-groove, 12-tongue-and-groove, 13-reverse turbine blade, 14-support ring.
Detailed Description
Referring to fig. 1 to 7, fig. 1 is a schematic view of the structure of the forward and reverse rotation turbine of the present invention, fig. 2 is a schematic view of the structure of the reverse rotation turbine blade disk of the present invention, fig. 3 is a schematic view of the structure of the reverse rotation turbine blade disk of the present invention in forward rotation, fig. 4 is a schematic view of the structure of the reverse rotation turbine blade disk in reverse rotation, fig. 5 is a schematic view of the flow direction of turbine gas in forward rotation of the forward rotation turbine of the present invention, fig. 6 is a schematic view of the flow direction of turbine gas in reverse rotation of the forward rotation turbine of the present invention, fig. 7 is a schematic view of the structure of the forward rotation turbine gas inlet housing of the present invention, the present invention provides a forward and reverse rotation turbine including a forward rotation turbine gas outlet housing 1, a forward and reverse rotation radial bearing 2, a forward and reverse rotation thrust bearing 3, a nozzle cap 4, a forward rotation turbine gas inlet housing 5, a forward rotation turbine gas inlet control valve 6, a reverse rotation turbine outlet control valve 7, a forward rotation turbine blade 8, a reverse rotation blade disk 9 and an adjustable flow area nozzle ring 10, the nozzle cover 4 is arranged on the forward turbine gas exhaust shell 1, the forward turbine gas inlet shell 5 is arranged on the forward turbine gas exhaust shell 1, the adjustable flow area nozzle ring 10 is arranged on the forward turbine gas inlet shell 5, the forward turbine gas inlet control valve 6 is arranged on the forward turbine gas inlet shell 5, the reverse turbine exhaust control valve 7 is also arranged on the forward turbine gas inlet shell 5, the forward and reverse rotation radial bearing 2 is arranged on a radial forward and reverse rotation bearing seat of the forward turbine gas exhaust shell 1, the forward and reverse rotation thrust bearing 3 is arranged on an axial forward and reverse rotation bearing seat of the forward turbine gas exhaust shell 1, the reverse rotation turbine blade disc 9 is arranged on a turbine shaft, the forward rotating turbine blades 8 are arranged on the reverse rotating turbine blade disk 9;
the nozzle cover 4 is designed into an expanding flow passage, the inner ring of the nozzle cover 4 is matched with the forward rotation turbine blades 8, and the outer ring of the nozzle cover 4 is matched with the reverse rotation turbine air inlet shell;
the reversing turbine blade 13 is integrally milled by a turbine disk, and the root of the reversing turbine blade 13 is designed with a special fillet so as to reduce stress concentration.
For this embodiment, the gas inlet casing 5 of the forward turbine is designed into a rotary structure, wherein the outer cavity is a gas inlet flow channel of the forward turbine, the inner cavity is a gas exhaust flow channel of the reverse turbine, the same casing is skillfully designed to realize the gas inlet of the forward turbine, and simultaneously realize the gas exhaust of the reverse turbine, the number of the casings is reduced, the reliability of the turbine structure is improved, the reverse turbine blades 13 are integrally milled by a turbine disc, the number and the blade shape of the reverse turbine blades 13 are specially designed, the root parts of the reverse turbine blades 13 are designed with special round corners, so as to reduce the root stress concentration of the reverse turbine blades 13, and meanwhile, the reverse turbine blades 13 are designed to give consideration to the pneumatic efficiency and the structural strength of the reverse turbine blades 13, and simultaneously reduce the rotational inertia of the rotor, the gas inlet casing 5 of the reverse turbine is also the gas exhaust casing of the reverse turbine, firstly, the forward turbine starts working, the forward turbine starts to operate, the reverse turbine starts to turn, the reverse turbine starts automatically, the working state of the reverse turbine is judged by a control program, if the reverse turbine is detected, the reverse turbine blades automatically, the reverse turbine needs to be opened, the gas inlet valve 6 is controlled by the control valve 6, and the gas inlet valve 6 is opened, and the gas inlet valve 6 is controlled by the reverse turbine 6, and the gas inlet valve 6 is opened by the reverse turbine valve 6, and the gas inlet valve 6 is controlled by the control valve 6, and the gas inlet valve 6 is opened by the reverse turbine valve 6, the high-temperature gas flows through the adjustable flow area nozzle ring 10 through the air inlet flow passage of the forward rotating turbine gas inlet shell 5, blows the turbine to do work, and the turbine rotates forward, because the reverse rotating turbine exhaust control valve 7 does not leak from the reverse rotating turbine exhaust flow passage, when the turbine rotates reversely, the reverse rotating turbine exhaust control valve 7 is opened, the forward rotating turbine gas inlet control valve 6 is closed, air flow enters from the reverse rotating turbine air inlet flow passage, and directly blows the reverse rotating turbine, so that the turbine shaft rotates reversely, the problems that the traditional turbine structure such as a turbocharger, a turbine and the like cannot realize the coaxial forward and reverse rotation function, and the forward and reverse rotation can be realized by adopting two shafts or changing the angle of a moving blade are solved, and the technical problems of great technical difficulty and low reliability exist;
the forward turbine gas inlet control valve 6 and the reverse turbine exhaust control valve 7 are designed as high-temperature-resistant butterfly valves, and are driven by a driving motor to execute opening and closing actions, and a control valve handle and a valve rod are both coated with heat-resistant and corrosion-resistant coatings so as to prevent fatigue failure caused by high-temperature gas impact corrosion during long-term operation in a high-temperature environment.
Further, the counter-rotating turbine blade disk 9 is provided with a dovetail groove 11, the forward-rotating turbine blade 8 is provided with a dovetail tooth 12, and the dovetail tooth 12 is placed in the dovetail groove 11;
the counter-rotating turbine blade disk 9 comprises counter-rotating turbine blades 13 and a support ring 14, the counter-rotating turbine blades 13 being arranged on a turbine shaft, the support ring 14 being arranged on the counter-rotating turbine blades 13.
For the present embodiment, the support ring 14 is fixed to the turbine shaft by the counter-rotating turbine blades 13, and the support ring 14 is used for mounting the forward-rotating turbine blades 8.
Further, the forward and reverse rotation radial bearing 2 and the forward and reverse rotation thrust bearing 3 are both provided with oil wedge surfaces, and the oil wedge surfaces of the forward and reverse rotation radial bearing 2 and the forward and reverse rotation thrust bearing 3 are both designed into symmetrical structures, namely, the forward rotation and the reverse rotation of the turbine shaft can both realize the function of supporting the rotor and providing thrust.
For this embodiment, the forward and reverse rotation radial bearing 2 is designed as a floating bearing, and three oil wedges are symmetrically arranged, so that the forward and reverse rotation of the turbine shaft can generate wedge-shaped convergence gaps to form oil film supporting force, the forward and reverse rotation thrust bearing 3 is designed as a full floating type, and the 6 oil wedges are symmetrically arranged, that is, the forward and reverse rotation of the turbine shaft can generate axial thrust.
Further, there is an interference between the adjustable flow area nozzle ring 10 and the nozzle housing 4.
For this embodiment, the adjustable flow area nozzle ring 10 is designed to be capable of adjusting the flow area, and meanwhile, the adjustable flow area nozzle ring 10 can achieve a complete closing function, that is, when the adjustable flow area nozzle ring 10 can be in a complete closing state, the air flow cannot leak from the adjustable flow area nozzle ring 10 through the forward rotating turbine blades 8 when the reverse rotating turbine blades 13 are in operation.
Referring to fig. 8, fig. 8 is a flow chart illustrating steps of a method for controlling a forward/reverse turbine according to the present invention, and the method for controlling a forward/reverse turbine according to the present invention includes the following steps:
step one: firstly, starting the forward and reverse rotation turbine to start working, wherein the initial rotation is forward rotation when the forward and reverse rotation turbine is started;
step two: automatically judging the working state of the forward and reverse rotation turbine through a control program;
step three: if the positive and negative rotation turbine needs to be reversed, the control mechanism automatically opens the exhaust control valve 7 of the reverse rotation turbine and closes the gas inlet control valve 6 of the positive rotation turbine, so that the positive and negative rotation turbine is quickly changed from positive rotation to reverse rotation.
In the third step, the control mechanism is a driving motor, and the driving motor can cool the temperature of the driving motor through cooling water, so that the reliability of the driving motor is improved.
According to the invention, the reverse rotation turbine blade disc 9 is designed into the reverse rotation turbine blade 13 and the support ring 14, so that the coaxial reverse rotation function of the turbine is realized, the reverse rotation turbine is arranged in the nozzle cover 4, when the turbine rotates positively, the forward rotation turbine gas inlet control valve 6 is opened, the reverse rotation turbine exhaust control valve 7 is closed, the forward rotation of the turbine can be realized, when the reverse rotation is needed, the forward rotation turbine gas inlet control valve 6 is closed, the adjustable flow area nozzle ring 10 is closed, and meanwhile, the reverse rotation turbine exhaust control valve 7 is opened, so that the reverse rotation function can be realized, and the structure is simple and reliable.
The above disclosure is only a preferred embodiment of the present invention, and it should be understood that the scope of the invention is not limited thereto, and those skilled in the art will appreciate that all or part of the procedures described above can be performed according to the equivalent changes of the claims, and still fall within the scope of the present invention.
Claims (9)
1. A turbine with positive and negative rotation is characterized in that,
including corotation turbine gas exhaust shell, corotation radial bearing, corotation thrust bearing, nozzle cover, corotation turbine gas inlet shell, corotation turbine gas inlet control valve, reversal turbine exhaust control valve, corotation turbine blade, reversal turbine blade dish and adjustable flow area nozzle ring, the nozzle cover sets up on the corotation turbine gas exhaust shell, corotation turbine gas inlet shell sets up on the corotation turbine gas exhaust shell, adjustable flow area nozzle ring sets up on the corotation turbine gas inlet shell, corotation turbine gas inlet control valve sets up on the corotation turbine gas inlet shell, reversal turbine gas inlet control valve sets up on the corotation turbine gas inlet shell equally, corotation radial bearing sets up on the radial corotation bearing of corotation turbine gas exhaust shell, the corotation thrust bearing sets up on the axial corotation bearing of corotation turbine gas exhaust shell, the turbine blade dish sets up on the turbine shaft, the corotation turbine blade dish sets up on the reversal turbine blade dish.
2. The forward and reverse turbine as claimed in claim 1, wherein,
the counter-rotating turbine blade disk is provided with a mortise, the forward-rotating turbine blade is provided with a tenon tooth portion, and the tenon tooth portion is arranged in the mortise.
3. The counter-rotating turbine as claimed in claim 2, wherein,
the counter-rotating turbine blade disk includes counter-rotating turbine blades disposed on a turbine shaft and a support ring disposed on the counter-rotating turbine blades.
4. The forward and reverse turbine as claimed in claim 3, wherein,
the nozzle cover is designed into an expanding flow passage, the inner ring of the nozzle cover is matched with the blades of the forward turbine, and the outer ring of the nozzle cover is matched with the air inlet shell of the reverse turbine.
5. The forward and reverse turbine as claimed in claim 4, wherein,
the reversing turbine blade is integrally milled by a turbine disc, and the root of the reversing turbine blade is designed with a special fillet so as to reduce stress concentration.
6. The forward and reverse turbine as claimed in claim 5, wherein,
the forward and reverse rotation radial bearing and the forward and reverse rotation thrust bearing are both arranged to be oil wedge surfaces, and the forward and reverse rotation radial bearing and the oil wedge surfaces of the forward and reverse rotation thrust bearing are both designed to be symmetrical structures, namely, the forward rotation and the reverse rotation of the turbine shaft can both realize the function of supporting the rotor and providing thrust.
7. The forward and reverse turbine as claimed in claim 6, wherein,
an interference is arranged between the nozzle ring with the adjustable flow area and the nozzle cover.
8. A method for controlling a forward/reverse turbine according to claim 7, comprising the steps of:
step one: firstly, starting the forward and reverse rotation turbine to start working, wherein the initial rotation is forward rotation when the forward and reverse rotation turbine is started;
step two: automatically judging the working state of the forward and reverse rotation turbine through a control program;
step three: if the positive and negative rotation turbine needs to be reversed, the control mechanism automatically opens the exhaust control valve of the reverse rotation turbine and closes the gas inlet control valve of the positive rotation turbine, so that the positive and negative rotation turbine is quickly changed into reverse rotation from positive rotation.
9. The method for controlling a turbine in forward and reverse rotation according to claim 8,
in the third step, the control mechanism is a driving motor, and the driving motor can cool the temperature of the driving motor through cooling water, so that the reliability of the driving motor is improved.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311610620.2A CN117365661A (en) | 2023-11-29 | 2023-11-29 | Forward and reverse rotation turbine and control method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311610620.2A CN117365661A (en) | 2023-11-29 | 2023-11-29 | Forward and reverse rotation turbine and control method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117365661A true CN117365661A (en) | 2024-01-09 |
Family
ID=89402562
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311610620.2A Pending CN117365661A (en) | 2023-11-29 | 2023-11-29 | Forward and reverse rotation turbine and control method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117365661A (en) |
-
2023
- 2023-11-29 CN CN202311610620.2A patent/CN117365661A/en active Pending
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