CN112780410A - Compact type turbine compressor structure - Google Patents
Compact type turbine compressor structure Download PDFInfo
- Publication number
- CN112780410A CN112780410A CN202110134620.4A CN202110134620A CN112780410A CN 112780410 A CN112780410 A CN 112780410A CN 202110134620 A CN202110134620 A CN 202110134620A CN 112780410 A CN112780410 A CN 112780410A
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- CN
- China
- Prior art keywords
- turbine
- compressor
- rotor shaft
- flange
- gas
- 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.)
- Pending
Links
- 230000005540 biological transmission Effects 0.000 claims abstract description 10
- 238000002485 combustion reaction Methods 0.000 description 5
- 239000000446 fuel Substances 0.000 description 5
- 230000002411 adverse Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000007788 liquid Substances 0.000 description 2
- 239000007858 starting material Substances 0.000 description 2
- 239000000126 substance Substances 0.000 description 2
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/045—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
- F02C3/05—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module the compressor and the turbine being of the radial flow type
-
- 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
- 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
- F04D29/04—Shafts or bearings, or assemblies thereof
- F04D29/043—Shafts
- F04D29/044—Arrangements for joining or assembling shafts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
- F04D29/624—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention is suitable for the field of gas turbine equipment, and particularly relates to a compact turbine compressor structure which comprises a rotor shaft additionally provided with a flange; the rotor shaft is connected with a gas compressor and a turbine through a flange, and the gas compressor and the turbine are distributed on two sides of the flange and centered through the rotor shaft; the compressor is used for transmitting torque through a screw and is fixed through a compressor bolt; the turbine is transmitted and twisted through a transmission pin and fixed through a turbine bolt; when the turbine works, torque is transmitted to the flange surface through the transmission pin and is transmitted to the compressor bolt to drive the compressor rotor to rotate; the span of the turbine and the gas compressor is reduced, the load of a rotor shaft is reduced, the number of parts is reduced, the structure is simple, the cost is reduced, and the reliability is improved.
Description
Technical Field
The invention relates to the field of gas turbine equipment, in particular to a compact type turbine compressor structure.
Background
The gas turbine is an internal combustion type power machine which takes continuously flowing gas as a working medium to drive an impeller to rotate at a high speed and converts the energy of fuel into useful work, and is a rotary impeller type heat engine.
In the main flow of air and gas in a gas Turbine, only a gas Turbine cycle consisting of three major components, namely a Compressor (Compressor), a Combustor (Combustor) and a gas Turbine (Turbine), is called as a simple cycle. Most gas turbines use a simple cycle scheme.
The air compressor sucks air from the external atmospheric environment, and the air is compressed step by the axial flow type air compressor to be pressurized, and meanwhile, the air temperature is correspondingly increased; compressed air is pumped into a combustion chamber and is mixed with injected fuel to be combusted to generate high-temperature and high-pressure gas; then the gas or liquid fuel enters a turbine to do work through expansion, the turbine is pushed to drive the gas compressor and the external load rotor to rotate at a high speed, the chemical energy of the gas or liquid fuel is partially converted into mechanical work, and electric work is output. The exhaust gas discharged from the turbine discharges to the atmosphere to release heat naturally. Thus, the gas turbine converts the chemical energy of the fuel into thermal energy and also converts part of the thermal energy into mechanical energy. In a gas turbine, a compressor is driven by a gas turbine to perform work through expansion, and the compressor is a load of the turbine. In a simple cycle, the turbine generates about 1/2 to 2/3 of mechanical work to drive the compressor, and the remaining about 1/3 of mechanical work to drive the generator. When the gas turbine is started, external power is firstly needed, a starter generally drives the gas compressor, and the gas turbine can not work independently until the mechanical power generated by the gas turbine is greater than the mechanical power consumed by the gas compressor and the external starter is tripped.
Because the combustion chamber is arranged between the gas compressor and the turbine, the distance between the gas compressor and the turbine is larger, the structure of the product is longer, the span between the fulcrums is larger, the weight is increased, the structural load is increased, the service life is greatly influenced, and the problem of rotor vibration is also brought. That is, at present, the known compressor and turbine structure of the gas turbine engine is that the compressor and the turbine are split structures and are respectively and independently installed on a rotor shaft, so that the structure is complex, the load of the rotor shaft is large, and adverse effects are brought to the manufacturing cost and the service life.
Disclosure of Invention
The invention aims to provide a compact type turbocompressor structure to solve the problems in the background technology. In order to achieve the purpose, the invention provides the following technical scheme:
a compact type turbine compressor structure comprises a rotor shaft provided with a flange; the rotor shaft is connected with a gas compressor and a turbine through a flange, and the gas compressor and the turbine are distributed on two sides of the flange and centered through the rotor shaft; the compressor is used for transmitting torque through a screw and is fixed through a compressor bolt; the turbine is transmitted and twisted through a transmission pin and fixed through a turbine bolt.
The gas turbine engine gas compressor and turbine structure solves the problems that the gas compressor and the turbine of the prior known gas turbine engine are split structures and are respectively and independently arranged on a rotor shaft, the structure is complex, the load of the rotor shaft is large, and adverse effects are brought to the manufacturing cost and the service life.
When the turbine works, torque is transmitted to the flange surface through the transmission pin and is transmitted to the compressor bolt to drive the compressor rotor to rotate; the span of the turbine and the gas compressor is reduced, the load of a rotor shaft is reduced, the number of parts is reduced, the structure is simple, the cost is reduced, and the reliability is improved.
In the compact turbocompressor structure of the invention: the compressor is sleeved on the rotor shaft and detachably fixed. The air compressor is detachably installed through a connecting system.
Preferably: the connecting system comprises a fixing screw and a threaded sleeve;
the compressor is detachably mounted through a fixing screw on the connecting system; the fixed screw is inserted in the screw sleeve to detachably mount the gas compressor;
the screw sleeve is internally provided with threads matched with the fixing screw.
The number of the fixing screws is three, wherein the number of the fixing screws is two, four, five, six or the like besides three, and the number of the fixing screws is not limited as long as the fixing screws can be inserted into the threaded sleeves to detachably mount the gas compressor; the preferred set screws are provided in triplicate.
In the compact turbocompressor structure of the invention: the turbine is mounted on the flange through a turbine positioning surface.
Further scheme: and a plurality of adjusting gaskets are additionally arranged between the turbine positioning surface and the flange.
Preferably: the alignment shim is detachably mounted. The turbine locating surface is centered with the cylinder of the rotor shaft.
In the compact turbocompressor structure of the invention: the compressor and the turbine are mounted back-to-back.
Compared with the prior art, the compact type turbine compressor structure comprises a rotor shaft provided with a flange; the rotor shaft is connected with a gas compressor and a turbine through a flange, and the gas compressor and the turbine are distributed on two sides of the flange and centered through the rotor shaft; the compressor is used for transmitting torque through a screw and is fixed through a compressor bolt; the turbine is transmitted and twisted through a transmission pin and fixed through a turbine bolt; when the turbine works, torque is transmitted to the flange surface through the transmission pin and is transmitted to the compressor bolt to drive the compressor rotor to rotate; the span of the turbine and the gas compressor is reduced, the load of a rotor shaft is reduced, the number of parts is reduced, the structure is simple, the cost is reduced, and the reliability is improved. The problem of because have the combustion chamber in the middle of compressor and the turbine, so lead to between compressor and the turbine apart from great, make the structure of product longer, the span is great between the fulcrum, makes weight increase, and the structural load increases, and the life-span receives great influence, has brought rotor vibration simultaneously is solved.
Drawings
Fig. 1 is a schematic structural view of a compact turbo compressor structure of the present invention.
In the figure: 1, an air compressor; 2-a rotor shaft; 3-thread sleeve; 4-a drive pin; 5-fixing screws; 6-aligning the shim; 7-turbine positioning surface; 8-a turbine; 9-turbine bolt.
Detailed Description
The technical solution of the present invention will be described in further detail with reference to specific embodiments. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
Aiming at the problems that the compressor and the turbine of the prior known gas turbine engine are of split structures and are respectively and independently arranged on a rotor shaft, the structure is complex, the load of the rotor shaft is large, and adverse effects are brought to the manufacturing cost and the service life; the invention aims to provide a compact type turbocompressor structure which comprises the following components:
in the embodiment of the invention, as shown in fig. 1, a compact type turbine compressor structure comprises a rotor shaft 2 additionally provided with a flange; the rotor shaft 2 is connected with a gas compressor 1 and a turbine 8 through a flange, the gas compressor 1 and the turbine 8 are distributed on two sides of the flange and are centered through the rotor shaft 2;
the compressor 1 is fixed through a compressor bolt and is transmitted through a screw; the worm gear 8 is torque-transmitted by the drive pin 4 and is fixed by the worm gear bolt 9.
The number of the driving pins 4 is three, wherein, besides three, two, or four, or five, or six, etc. may be provided, and the number of the driving pins 4 is not limited as long as the turbine 8 can be transmitted through the driving pins 4, and preferably, three driving pins 4 are provided.
In the embodiment of the invention, when the turbine 8 works, the torque is transmitted to the flange surface through the transmission pin 4 and is transmitted to the bolt of the gas compressor to drive the rotor of the gas compressor 1 to rotate; the span of the turbine and the gas compressor is reduced, the load of a rotor shaft is reduced, the number of parts is reduced, the structure is simple, the cost is reduced, and the reliability is improved.
In the embodiment of the invention, as shown in fig. 1, the compressor 1 is sleeved on the rotor shaft 2 and detachably fixed; the compressor 1 is detachably mounted through a connecting system.
The connecting system comprises a fixing screw 5 and a threaded sleeve 3; the compressor 1 is detachably mounted through a fixing screw 5 on the connecting system; the fixing screw 5 is inserted in the screw sleeve 3 to detachably mount the gas compressor 1; the screw sleeve 3 is internally provided with threads matched with the fixing screw 5.
The number of the fixing screws 5 is three, wherein two, four, five, six or the like can be provided besides three, and the number of the fixing screws is not limited as long as the fixing screws 5 can be inserted into the screw sleeve 3 to detachably mount the gas compressor 1; the preferred set screws 5 are provided in triplicate.
In the compact turbocompressor structure of the invention: the turbine 8 is mounted on the flange through the turbine positioning surface 7. And a plurality of alignment gaskets 6 are additionally arranged between the turbine positioning surface 7 and the flange. The alignment shim 6 is detachably mounted. The turbine positioning surface 7 is centered with the cylinder of the rotor shaft 2.
The number of the alignment pads 6 is not limited, and the number of the alignment pads 6 is two, three, four, or five, and preferably three.
The compressor 1 and the turbine 8 are mounted back-to-back.
The invention relates to a compact type turbine compressor structure, which comprises a rotor shaft 2 provided with a flange; the rotor shaft 2 is connected with a gas compressor 1 and a turbine 8 through a flange, the gas compressor 1 and the turbine 8 are distributed on two sides of the flange and are centered through the rotor shaft 2; the compressor 1 is fixed through a compressor bolt and is transmitted through a screw; the turbine 8 is transmitted through the transmission pin 4 and fixed through a turbine bolt 9; when the turbine 8 works, torque is transmitted to the flange surface through the transmission pin 4 and is transmitted to the compressor bolt, and the rotor of the compressor 1 is driven to rotate; the span of the turbine and the gas compressor is reduced, the load of a rotor shaft is reduced, the number of parts is reduced, the structure is simple, the cost is reduced, and the reliability is improved. The problem of because have the combustion chamber in the middle of compressor and the turbine, so lead to between compressor and the turbine apart from great, make the structure of product longer, the span is great between the fulcrum, makes weight increase, and the structural load increases, and the life-span receives great influence, has brought rotor vibration simultaneously is solved.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
While the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.
Claims (9)
1. A compact turbocompressor structure is characterized in that,
comprises a rotor shaft additionally provided with a flange;
the rotor shaft is connected with a gas compressor and a turbine through a flange, and the gas compressor and the turbine are distributed on two sides of the flange and centered through the rotor shaft;
the compressor is used for transmitting torque through a screw and is fixed through a compressor bolt;
the turbine is transmitted and twisted through a transmission pin and fixed through a turbine bolt.
2. The compact turbocompressor structure according to claim 1, characterized in that the compressor is fitted over the rotor shaft and is detachably fixed.
3. A compact turbocompressor structure according to claim 2, characterized in that the compressor is detachably mounted by means of a connection system.
4. A compact turbocompressor structure according to claim 3,
the connecting system comprises a fixing screw and a threaded sleeve;
the compressor is detachably mounted through a fixing screw on the connecting system; the fixed screw is inserted in the screw sleeve to detachably mount the gas compressor;
the screw sleeve is internally provided with threads matched with the fixing screw.
5. A compact turbocompressor structure according to claim 1, characterized in that the turbine is mounted on the flange via a turbine locating surface.
6. The compact turbocompressor structure according to claim 5, characterized in that alignment shims are additionally arranged between the turbine positioning surface and the flange.
7. The compact turbocompressor structure according to claim 6, characterized in that the alignment washer is detachably mounted.
8. A compact turbocompressor structure according to claim 5, characterised in that the turbine locating surface is centred on the cylinder of the rotor shaft.
9. A compact turbocompressor according to any of claims 1-8, characterised in that the compressor and turbine are mounted back-to-back.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110134620.4A CN112780410A (en) | 2021-01-29 | 2021-01-29 | Compact type turbine compressor structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110134620.4A CN112780410A (en) | 2021-01-29 | 2021-01-29 | Compact type turbine compressor structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112780410A true CN112780410A (en) | 2021-05-11 |
Family
ID=75760238
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110134620.4A Pending CN112780410A (en) | 2021-01-29 | 2021-01-29 | Compact type turbine compressor structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112780410A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114033553A (en) * | 2021-09-22 | 2022-02-11 | 浙江意动科技股份有限公司 | Turbojet engine rotor transmission shaft and axial locking device thereof |
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2021
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