CN104533624A - Axial flow turbine disc shaft of micro-turbine jet engine - Google Patents
Axial flow turbine disc shaft of micro-turbine jet engine Download PDFInfo
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- CN104533624A CN104533624A CN201410767729.1A CN201410767729A CN104533624A CN 104533624 A CN104533624 A CN 104533624A CN 201410767729 A CN201410767729 A CN 201410767729A CN 104533624 A CN104533624 A CN 104533624A
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- turbine
- axial flow
- turbine disc
- rotating shaft
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Abstract
The invention belongs to the field of micro-turbine jet engines, and particularly relates to an axial flow turbine disc shaft of a micro-turbine jet engine. The axial flow turbine disc shaft comprises a turbine disc, a blade and a rotating shaft, wherein the turbine disc and the blade are precisely cast into a whole, a center blind hole is formed in the center of the turbine disc, a position lug boss is arranged at the end part, which is connected with the turbine disc, of the rotating shaft, and is inserted into the center blind hole, and the connecting surface of the end face of the rotating shaft and the turbine disc are welded and fixed by virtue of a vacuum electronic beam. The axial flow turbine disc shaft provided by the invention has the advantages that due to adoption of a disc and shaft integrated structure, processing, assembling and structure are simplified, materials and work hour are saved, the manufacturing cost is lowered, the workpiece quality is ensured, a rotor structure is dynamically balanced, and the stress distribution, the vibration characteristic and the service life are improved.
Description
Technical field
The invention belongs to Micro Turbine Jet Engine field, specifically a kind of Micro Turbine Jet Engine axial flow turbine dish axle.
Background technique
Micro Turbine Jet Engine generally refers to diameter 6-20 centimetre, the motor within the scope of thrust 5 ~ 1000N.Usually at compressor pressure ratio lower than 4.0, when air mass flow is greater than 500g/s, Micro Turbine Jet Engine adopts axial flow turbine, and its advantage is: structure is simple, lightweight, and thrust-mass ratio is large, and flow losses are little, and efficiency is high.
By the retrieval of domestic and international publication as: the integral structure adopting centrifugal turbine and rotor shaft in vehicle supercharger is only proposed in number of patent application 02122017.4.Do not relate to the integral structure of miniature turbine jet engines axial flow turbine and axle; The integral structure adopting centrifugal turbine and rotor shaft in vehicle supercharger is also only proposed in number of patent application 201080028213.5, and its process structure feature that should be mentioned that dish, axle friction welding surface of contact more; The method that number of patent application 97125874.0 and 200810110548.6 proposes directly to adopt mechanical interference to connect realizes the connection between titanium-aluminum alloy turbine and the rotating shaft of 42CrMo alloy; Number of patent application 201310166758.8 proposes interference thread and the anti-loosening method that combines of pin and structure and solves connection between titanium-aluminum alloy turbine and the rotating shaft of 42CrMo alloy.It can thus be appreciated that above patent does not all propose to adopt the turbine disk, axle integral structure in Micro Turbine Jet Engine structure.
Be same as conventional jet motor as its working principle of Micro Turbine Jet Engine, it is characterized in that the macro of size, weight and the simplification of structure.Working procedure is that turbine drives gas compressor pressurized air, and high-pressure air flows through firing chamber oil jetting combustion heating and becomes high-temperature high-pressure fuel gas, drives turbine work done, then produces thrust by jet pipe high velocity jet.Its operating temperature is 700 DEG C-900 DEG C, and working speed is 50000-100000 rev/min.Under high temperature like this, high rotating speed, the rotor of Micro Turbine Jet Engine is made separate piece usually, and namely axial flow turbine dish, the independent manufacturing of rotor shaft, then, be assembled into rotor assembly.Obviously, this makes its structure, processing, assembling complicated, and consumptive material is comparatively large, and dish, shaft concentricity are difficult to ensure, add dynamically balanced difficulty.
Summary of the invention
The problem to be solved in the present invention how to make the dynamic balancing of rotor structure, stress distribution, vibration characteristics, working life all be improved, and provides a kind of Micro Turbine Jet Engine axial flow turbine dish axle.
Present invention employs following technological scheme:
Micro Turbine Jet Engine axial flow turbine dish axle, it comprises the turbine disk, blade and rotating shaft, the turbine disk and blade precision casting one, turbine disk center is provided with central blind hole, the end that rotating shaft is connected with the turbine disk is provided with positioning boss, positioning boss inserts in central blind hole, and the junction surface of rotating shaft end face and the turbine disk is welded and fixed by electron-bombardment welding.
Described rotating shaft two ends side face is provided with bearing surface, is provided with cylndrical surface between two bearing surfaces, and the diameter of cylndrical surface is less than the diameter of bearing surface.
Described cylndrical surface is lower than bearing surface 0.12mm.
Advantage of the present invention is this dish, axle integrative-structure has simplified processing, assembling and structure, saves material and man-hour, and reduce manufacture cost, ensure that workpiece quality, make the dynamic balancing of rotor structure, stress distribution, vibration characteristics, working life is all improved.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Embodiment
As shown in Figure 1, Micro Turbine Jet Engine axial flow turbine dish axle, it comprises the turbine disk 1, blade 2 and rotating shaft 3, the turbine disk 1 and blade 2 precision casting one, the turbine disk 1 center is provided with central blind hole, the end that rotating shaft 3 is connected with the turbine disk 1 is provided with positioning boss e, positioning boss e inserts in central blind hole, to ensure and the welding quality of raising dish axle, be that the fit tolerance that positioning center hole and centralized positioning boss adopt is (H6/f5), its function is guarantee dish shaft concentricity, reduces welding biased error; The junction surface of rotating shaft 3 end face and the turbine disk is welded and fixed by electron-bombardment welding, have electron beam weld 4, this overall structure has simplified processing, assembling and structure, saves material and man-hour, improve the structural behaviour of rotor part, application vacuum electron beam welding.The chemical composition stability of weld seam and pure, joint strength is high, and weldquality is high; Electron beam welding speed is fast, and heat affected zone is little, and welding heat distortion is little, improves manufacturing efficiency and quality of product; Described rotating shaft 3 two ends side face is provided with bearing surface a and c, cylndrical surface b is provided with between two bearing surfaces a, c, the diameter of cylndrical surface b is less than the diameter of bearing surface a, c, rotating shaft 3 and the side face of the turbine disk 1 connecting end are also provided with closure gasket groove, described cylndrical surface is lower than bearing surface 0.12mm, its role is to reduce fine finishing amount, be convenient to bearing is installed.
Claims (3)
1. Micro Turbine Jet Engine axial flow turbine dish axle, it comprises the turbine disk, blade and rotating shaft, it is characterized in that: the turbine disk and blade precision casting one, turbine disk center is provided with central blind hole, the end that rotating shaft is connected with the turbine disk is provided with positioning boss, positioning boss inserts in central blind hole, and the junction surface of rotating shaft end face and the turbine disk is welded and fixed by electron-bombardment welding.
2. Micro Turbine Jet Engine axial flow turbine dish axle according to claim 1, is characterized in that: described rotating shaft two ends side face is provided with bearing surface, is provided with cylndrical surface between two bearing surfaces, and the diameter of cylndrical surface is less than the diameter of bearing surface.
3. Micro Turbine Jet Engine axial flow turbine dish axle according to claim 2, is characterized in that: described cylndrical surface is lower than bearing surface 0.12mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410767729.1A CN104533624A (en) | 2014-12-12 | 2014-12-12 | Axial flow turbine disc shaft of micro-turbine jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410767729.1A CN104533624A (en) | 2014-12-12 | 2014-12-12 | Axial flow turbine disc shaft of micro-turbine jet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104533624A true CN104533624A (en) | 2015-04-22 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410767729.1A Pending CN104533624A (en) | 2014-12-12 | 2014-12-12 | Axial flow turbine disc shaft of micro-turbine jet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104533624A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106523154A (en) * | 2016-12-01 | 2017-03-22 | 从宏锦 | Airflow driving machine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20010027963A1 (en) * | 2000-03-13 | 2001-10-11 | Haruo Bazukuri | Method of machining the turbine rotor shaft of a supercharger |
| US20060067824A1 (en) * | 2004-09-30 | 2006-03-30 | O'hara Stephen J | Turbocharger with titanium component |
| US7156282B1 (en) * | 2005-10-11 | 2007-01-02 | Honeywell International, Inc. | Titanium-aluminide turbine wheel and shaft assembly, and method for making same |
| CN101092882A (en) * | 2007-07-12 | 2007-12-26 | 刘天成 | Electron bombardment welding turbine shaft, and producing technique |
| CN202431360U (en) * | 2012-01-18 | 2012-09-12 | 山东富源动力设备有限公司 | Improved turbine shaft of supercharger |
| CN204371494U (en) * | 2014-12-12 | 2015-06-03 | 常州环能涡轮动力股份有限公司 | Micro Turbine Jet Engine axial flow turbine dish axle |
-
2014
- 2014-12-12 CN CN201410767729.1A patent/CN104533624A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20010027963A1 (en) * | 2000-03-13 | 2001-10-11 | Haruo Bazukuri | Method of machining the turbine rotor shaft of a supercharger |
| US20060067824A1 (en) * | 2004-09-30 | 2006-03-30 | O'hara Stephen J | Turbocharger with titanium component |
| US7156282B1 (en) * | 2005-10-11 | 2007-01-02 | Honeywell International, Inc. | Titanium-aluminide turbine wheel and shaft assembly, and method for making same |
| CN101092882A (en) * | 2007-07-12 | 2007-12-26 | 刘天成 | Electron bombardment welding turbine shaft, and producing technique |
| CN202431360U (en) * | 2012-01-18 | 2012-09-12 | 山东富源动力设备有限公司 | Improved turbine shaft of supercharger |
| CN204371494U (en) * | 2014-12-12 | 2015-06-03 | 常州环能涡轮动力股份有限公司 | Micro Turbine Jet Engine axial flow turbine dish axle |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106523154A (en) * | 2016-12-01 | 2017-03-22 | 从宏锦 | Airflow driving machine |
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Application publication date: 20150422 |
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| RJ01 | Rejection of invention patent application after publication |