CN2505601Y - Spindle shaft of core rotor of gas-turbine engine - Google Patents
Spindle shaft of core rotor of gas-turbine engine Download PDFInfo
- Publication number
- CN2505601Y CN2505601Y CN 01275915 CN01275915U CN2505601Y CN 2505601 Y CN2505601 Y CN 2505601Y CN 01275915 CN01275915 CN 01275915 CN 01275915 U CN01275915 U CN 01275915U CN 2505601 Y CN2505601 Y CN 2505601Y
- Authority
- CN
- China
- Prior art keywords
- shaft
- turbine engine
- gas turbine
- annulate shaft
- outer annulate
- 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.)
- Expired - Fee Related
Links
- 239000006185 dispersion Substances 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 37
- 239000002737 fuel gas Substances 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 230000017525 heat dissipation Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 238000002485 combustion reaction Methods 0.000 description 2
- 230000000916 dilatatory effect Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
- 239000011148 porous material Substances 0.000 description 1
- 239000002912 waste gas Substances 0.000 description 1
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A spindle shaft of core rotor of gas-turbine engine comprises an outer collared shaft, an inner collared shaft and a plurality of high-pressure turbine rotor blades, wherein, the diameter of the inner collared shaft is less than that of the outer collared shaft, and the high-pressure turbine rotor blades are extended outward from the inner collared shaft at radial direction and connected with the posterior segment of the outer collared shaft, so as to make the inner collared shaft coaxially arranged inside the posterior segment of the outer collared shaft. The utility model increases the diameter of the outer collared shaft, which can improve the rigidity and the critical speed of a rotating shaft. The utility model can also make a tank-shaped burner arranged in a hollow holding chamber of the outer collared shaft, which can effectively utilize space to meet the requirements for compact design, and reduces heat dispersion to improve the heat efficiency of gas-turbine engines.
Description
Technical field
The utility model relates to a kind of turning shaft structure, especially refer to a kind of turning shaft structure that is common to the central rotor (Engine Core Rotor) of gas turbine engine (GasTurbine Engine), be applicable to the gas turbine engine of axial flow (Axial Type) compressor or centrifugal (Centrifugal Type) compressor.
Background technique
Fig. 1 show a gas turbine engine 9 by compressing section 91, burning zone 92, and institute such as turbine section 93 form.Be illustrated as the axial flow gas turbine engine 9 of conventional known, be in a casing 94 (Casing) central rotor 95 to be set, the central rotating shaft 950 (Shaft) of central rotor 95 and 94 of casings are formed with an annulus so as to being installed with known annular burner 96 (Annular Combustor).
Air is via the dilating effect of casing 94 leading portion compressor stator blades 941 (Compressor Stator Blade), pass through high pressure compressor rotor blade 951 (HPC Rotor Blade) work done again and form pressurized gas, and enter burning in the annular burner 96 and the generation high-temperature high-pressure fuel gas.When this high-temperature high-pressure fuel gas is flowed through High Pressure Turbine Rotor blade 952 (HPT Rotor Blade), can impel its rotation to central rotating shaft 950 works done, the while and the power rotor blade 971 of flowing through are to urge its rotation with output power to power rotor 97 works done.
Yet, the annular burner 96 of above-mentioned known gas turbine engine 9 is the peripheries that are surrounded on central rotating shaft 950, therefore central rotating shaft 950 diameters are little, difficult strengthens, cause central rotating shaft 950 rigidity own to promote, and the critical speed of rotation of central rotating shaft 950 also can't improve, and this phenomenon especially betides on the high-revolving miniature gas turbine engine.
In addition, the annular burner 96 of known gas turbine engine 9 must be disposed in the annulus of 950 of casing 94 and central rotating shafts separately, took up space on foot again the trouble in 960 minutes except making annular burner, can't reach space compact design (Compact Design) requirement, and annular burner 96 is coated on central rotating shaft 950 peripheries, is easy to generate the heat dissipation problem.Below all non-very good.
Summary of the invention
Main purpose of the present utility model is to provide a kind of turning shaft structure of gas turbine engine central rotor, can increase the rotating shaft diameter, thereby improves rotating shaft rigidity and critical speed of rotation, and then increases rotating shaft stability and working life.
Another purpose of the present utility model is to provide a kind of turning shaft structure of gas turbine engine central rotor, burner directly can be installed on rotating shaft inside, thereby effectively utilize the space to reach the compact design requirement, can reduce heat dissipation again to improve the thermal efficiency of gas turbine engine.
Above-mentioned purpose of the present utility model is achieved in that a kind of turning shaft structure of gas turbine engine central rotor, it is characterized in that, comprising:
One outer annulate shaft generally is hollow and annular body and extension vertically, and described outer annulate shaft comprises a leading portion, reaches a back segment, and forms a medium altitude chamber at middle intersegmental part;
One inner axle, diameter is less than the back segment of described outer annulate shaft; And
A plurality of High Pressure Turbine Rotor blades, be fixedly arranged between the back segment and described inner axle of described outer annulate shaft, each High Pressure Turbine Rotor blade is extended radially outwardly by described inner axle respectively and is linked to the back segment of described outer annulate shaft, the coaxial back intersegmental part that is mounted on described outer annulate shaft of described inner axle.
The turning shaft structure of gas turbine engine central rotor described in the utility model wherein also comprises a burner, and described burner is located in the described medium altitude chamber of described outer annulate shaft.
The turning shaft structure of gas turbine engine central rotor described in the utility model, wherein said burner are the burners that is jar shape.
The turning shaft structure of gas turbine engine central rotor described in the utility model wherein also includes:
Annulate shaft before one, diameter is less than the leading portion of described outer annulate shaft; And
A plurality of high pressure compressor rotor blades, be fixedly arranged between the leading portion and described preceding annulate shaft of described outer annulate shaft, each high pressure compressor rotor blade is extended radially outwardly by annulate shaft before described respectively and is linked to the leading portion of described outer annulate shaft, the described preceding coaxial preceding intersegmental part that is mounted on described outer annulate shaft of annulate shaft.
The turning shaft structure of gas turbine engine central rotor described in the utility model, wherein said gas turbine engine are the gas turbine engine of an Axial Flow Compressor.
The turning shaft structure of gas turbine engine central rotor described in the utility model, wherein said gas turbine engine are the gas turbine engine of a centrifugal compressor.
This shows that the turning shaft structure of gas turbine engine central rotor of the present utility model includes an outer annulate shaft, an inner axle and a plurality of High Pressure Turbine Rotor blade.Wherein, outer annulate shaft generally is the hollow and annular body and extends vertically, and it includes a leading portion, reaches a back segment, and forms a medium altitude chamber at middle intersegmental part; The diameter of inner axle is less than the back segment of outer annulate shaft; Described High Pressure Turbine Rotor vanes fixed is arranged between the back segment and inner axle of outer annulate shaft, each High Pressure Turbine Rotor blade is extended radially outwardly by inner axle respectively and is linked to the back segment of outer annulate shaft, so that with the coaxial back intersegmental part that is mounted on outer annulate shaft of inner axle.
Because the utility model changes the outer shroud shaft diameter is strengthened, therefore can improve rotating shaft rigidity and critical speed of rotation, and then increase rotating shaft stability and working life.
The utility model also can be located in one jar of shape burner in the medium altitude chamber of outer annulate shaft, therefore can effectively utilize the space to reach compact design and require, can reduce again heat dissipation to improve the thermal efficiency of gas turbine engine.
In addition, the utility model also can be set up the less preceding annulate shaft of a diameter, so that extend radially outwardly a plurality of high pressure compressor rotor blades being linked to the leading portion of outer annulate shaft by preceding annulate shaft, so as to the coaxial preceding intersegmental part that is mounted on outer annulate shaft of preceding annulate shaft.
Description of drawings
Fig. 1 is the schematic representation of common shaft streaming gas turbine engine;
Fig. 2 is the schematic representation that a preferred embodiment of the turning shaft structure of gas turbine engine central rotor described in the utility model is used in the axial flow gas turbine engine;
Fig. 3 is the detail structure chart that another preferred embodiment of the turning shaft structure of gas turbine engine central rotor described in the utility model is used in centrifugal gas turbine engine.
Embodiment
In order more to understand technology contents of the present utility model, describe especially exemplified by two preferred embodiment.
As shown in Figure 2, it is the preferred embodiment schematic representation of the utility model gas turbine engine (Axial Type Gas Turbine Engine) of being used in an Axial Flow Compressor, surpass 60 with a rotating speed especially in this example, the miniature gas turbine engine of 000rpm (below 200 lbt, or the output of 250 horsepower shaft works is following) is illustrated for example.Diagram central rotor 71 (Engine CoreRotor) is mounted in the casing 72 (Casing), casing 72 leading portions are compressing section 73 (Compression Section), the stage casing is burning zone 74 (Combustion Section), and back segment is turbine section 75 (Turbine Section).
The rotating shaft of above-mentioned central rotor 71 (Shaft) is made up of outer annulate shaft 1, inner axle 2, a plurality of High Pressure Turbine Rotor blade 3 (HPT Rotor Blade), preceding annulate shaft 5, a plurality of high pressure compressor rotor blade 6 (HPC Rotor Blade) and burner 4 (Combustor).
Wherein, outer annulate shaft 1 has than major diameter, and it generally is the hollow and annular body and extends vertically, has a leading portion 11, a back segment 12, and forms a medium altitude chamber 13 at middle intersegmental part.Burner 4 just can be located in the medium altitude chamber 13, and the preferably is to use a kind of traditional jar shape burner 4 (Can TypeCombustor) to save manufacture cost.
Before 5 coaxial outer annulate shaft 1 leading portion 11 inside that are mounted on of annulate shaft, preceding annulate shaft 5 diameters are less than outer annulate shaft 1 leading portion 11 internal diameters, and are extended radially outward by preceding annulate shaft 5 and link by a plurality of high pressure compressor rotor blades 6 and be fixedly arranged on outer annulate shaft 1 leading portion 11 inside.
When the compressing section 73 of air by casing 72 front ends enters, through the dilating effect (Diffusion Effect) of compressor stator blade 731 (Compressor Stator Blade), and form pressurized gas through high pressure compressor rotor blade 6 (HPC Rotor Blade) works done, and enter in jar shape burner 4 burning to produce high-temperature high-pressure fuel gas.This high-temperature high-pressure fuel gas is flowed through High Pressure Turbine Rotor blade 3 (HPT Rotor Blade) fast so that the rotating shaft work done of central rotor 71 is made its rotation, and while and the power rotor blade 81 of flowing through (Power Turbine Blade) are so that 8 works done impel its rotation with output power to power rotor.
The utility model is with outer annulate shaft 1 enlarged diameter, again in front and back two ends organize respectively the preceding annulate shaft 5 that is provided with than path, with inner axle 2, the diameter itself that therefore outer annulate shaft 1 increases has bigger rigidity, and can design in a critical speed of rotation (Critical Speed) operation down, the stability of a system improves can increase working life again.
In addition, the utility model is because outer annulate shaft 1 enlarged diameter so burner 4 directly can be installed on outer annulate shaft 1 inside, can effectively utilize the space to reach compact design (Compact Design) requirement.For the gas turbine engine of identical output power, overall volume of the present utility model and weight can significantly be reduced, and according to experiment, are about 80% of traditional gas turbine engine, or are 20% of diesel motor.
Again, the utility model is coated on outer annulate shaft 1 and casing 72 inside with burner 4, can effectively improve the heat dissipation problem, has improved the thermal efficiency of gas turbine engine relatively, all promotes effect than known technology.
Fig. 3 is another embodiment of the utility model, is to use in the turning shaft structure of the gas turbine engine central rotor of one centrifugal (Centrifugal Type) compressor.This example annulate shaft 10 back segments 120 inside is equally outside fixed an inner axle 20 by a plurality of High Pressure Turbine Rotor blades 30 of radial distribution with binding, and outer annulate shaft 10 inside also are installed with a burner 40.Yet, please note that outer annulate shaft 10 leading portions of this example are directly to be locked on the compressor drum 50.
After the centrifugal force work done pressurization of air by compressor drum 50, promote temperature via heat exchanger 76, flow through again groove on the outer annulate shaft 10, and enter burner 40 internal combustion to form high-temperature high-pressure fuel gas by pore 401, the High Pressure Turbine Rotor blade 30 of flowing through again rotates its inner axle 20, outer annulate shaft 10 in the lump, and the power rotor blade 810 of flowing through simultaneously impels power rotor 80 rotation with output power, and last waste gas flows into peripheral heat exchanger 76 to carry out after the heat exchange and discharge extraneous by air outlet flue 721.This example also strengthens outer annulate shaft 10 diameters, so that be installed with burner 40 in inside, also can reach above-mentioned purpose and effect.
In sum, the utility model is purpose, means and effect no matter, show that all it is totally different in the feature of known technology, and above-mentioned many embodiments give an example for convenience of explanation, the interest field that the utility model is advocated should be as the criterion so that claim is described, but not only limits to the foregoing description.
Claims (6)
1. the turning shaft structure of a gas turbine engine central rotor is characterized in that, comprising:
One outer annulate shaft generally is hollow and annular body and extension vertically, and described outer annulate shaft comprises a leading portion, reaches a back segment, and forms a medium altitude chamber at middle intersegmental part;
One inner axle, diameter is less than the back segment of described outer annulate shaft; And
A plurality of High Pressure Turbine Rotor blades, be fixedly arranged between the back segment and described inner axle of described outer annulate shaft, each High Pressure Turbine Rotor blade is extended radially outwardly by described inner axle respectively and is linked to the back segment of described outer annulate shaft, the coaxial back intersegmental part that is mounted on described outer annulate shaft of described inner axle.
2. the turning shaft structure of gas turbine engine central rotor as claimed in claim 1 is characterized in that, also comprises a burner, and described burner is located in the described medium altitude chamber of described outer annulate shaft.
3. the turning shaft structure of gas turbine engine central rotor as claimed in claim 2 is characterized in that, described burner is the burner that is jar shape.
4. the turning shaft structure of gas turbine engine central rotor as claimed in claim 1 is characterized in that, also includes:
Annulate shaft before one, diameter is less than the leading portion of described outer annulate shaft; And
A plurality of high pressure compressor rotor blades, be fixedly arranged between the leading portion and described preceding annulate shaft of described outer annulate shaft, each high pressure compressor rotor blade is extended radially outwardly by annulate shaft before described respectively and is linked to the leading portion of described outer annulate shaft, the described preceding coaxial preceding intersegmental part that is mounted on described outer annulate shaft of annulate shaft.
5. the turning shaft structure of gas turbine engine central rotor as claimed in claim 1 is characterized in that, described gas turbine engine is the gas turbine engine of an Axial Flow Compressor.
6. the turning shaft structure of gas turbine engine central rotor as claimed in claim 1 is characterized in that, described gas turbine engine is the gas turbine engine of a centrifugal compressor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01275915 CN2505601Y (en) | 2001-12-05 | 2001-12-05 | Spindle shaft of core rotor of gas-turbine engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 01275915 CN2505601Y (en) | 2001-12-05 | 2001-12-05 | Spindle shaft of core rotor of gas-turbine engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2505601Y true CN2505601Y (en) | 2002-08-14 |
Family
ID=33680210
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 01275915 Expired - Fee Related CN2505601Y (en) | 2001-12-05 | 2001-12-05 | Spindle shaft of core rotor of gas-turbine engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2505601Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100354503C (en) * | 2002-11-06 | 2007-12-12 | 通用电气公司 | Diffusion coupler cap of axial-connected turbine |
| CN100430606C (en) * | 2004-01-05 | 2008-11-05 | 财团法人工业技术研究院 | High-speed cantilever centrifugal compressor rotor mechanism |
-
2001
- 2001-12-05 CN CN 01275915 patent/CN2505601Y/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100354503C (en) * | 2002-11-06 | 2007-12-12 | 通用电气公司 | Diffusion coupler cap of axial-connected turbine |
| CN100430606C (en) * | 2004-01-05 | 2008-11-05 | 财团法人工业技术研究院 | High-speed cantilever centrifugal compressor rotor mechanism |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5081832A (en) | High efficiency, twin spool, radial-high pressure, gas turbine engine | |
| JP4906311B2 (en) | Counter-rotating gas turbine engine and method of assembling the same | |
| RU2648806C2 (en) | Engine | |
| CA2650511C (en) | Fan rotating blade for turbofan engine | |
| EP2025871B1 (en) | Centripetal turbine and internal combustion engine with such a turbine | |
| US4428715A (en) | Multi-stage centrifugal compressor | |
| JP2004512449A (en) | Apparatus and method for increasing turbine power | |
| CN101037960A (en) | High pressure ratio aft fan | |
| KR102126882B1 (en) | Nozzle assembly, combustor and gas turbine including the same | |
| US20080232949A1 (en) | Turbomachine Having an Axially Displaceable Rotor | |
| JP2008157237A (en) | Turbofan engine assembly | |
| WO2007103777A2 (en) | Two-shaft turbocharger | |
| CN1459556A (en) | Returnable pressurzing air compressor for gas turbine | |
| US5160080A (en) | Gas turbine engine and method of operation for providing increased output shaft horsepower | |
| CN112377268A (en) | Integrated diffuser for additive manufacturing | |
| CN112696269A (en) | Multi-rotor micro gas turbine and starting method thereof | |
| CN104948300A (en) | Combustion gas turbine | |
| CN2505601Y (en) | Spindle shaft of core rotor of gas-turbine engine | |
| CN100362225C (en) | Miniature single propeller turbine fan engine | |
| US6637209B2 (en) | Engine core rotor shaft structure for gas turbine engine | |
| CN211343135U (en) | Multistage turbine type micro gas turbine | |
| EP0452642B1 (en) | High efficiency, twin spool, radial-high pressure, gas turbine engine | |
| JP2020045789A (en) | Gas turbine blower/pump | |
| CN2454549Y (en) | Radial-flow turbine | |
| CN1924319A (en) | Rotary jet engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20020814 Termination date: 20101205 |