CN108547667B - It is a kind of without being preced with hollow single crystal turbine blade blade tip loading method - Google Patents
It is a kind of without being preced with hollow single crystal turbine blade blade tip loading method Download PDFInfo
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- CN108547667B CN108547667B CN201810283505.1A CN201810283505A CN108547667B CN 108547667 B CN108547667 B CN 108547667B CN 201810283505 A CN201810283505 A CN 201810283505A CN 108547667 B CN108547667 B CN 108547667B
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- single crystal
- turbine blade
- blade
- crystal turbine
- hollow single
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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
- 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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/83—Testing, e.g. methods, components or tools therefor
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- Engineering & Computer Science (AREA)
- Architecture (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to a kind of without the hollow single crystal turbine blade blade tip loading method of hat, specifically: before without hollow single crystal turbine blade casting is preced with, an integral shroud wax-pattern is welded on its wax-pattern, form combination wax-pattern, then the combination lost wax casting shrouded blade testpieces is utilized, the casting integral shroud of shrouded blade testpieces is inverted ladder-shaped body structure, inside the airflow channel that is smoothly discharged with cooling air-flow inside guaranteed hollow single crystal turbine blade.After the casting integral shroud of shrouded blade testpieces is connect with point half internal clamping block for designed special fixture, the inverted ladder-shaped body cavity being packed into the middle part of whole outer fixture block may be implemented to load without the hollow single crystal turbine blade blade tip of hat by designed special fixture.It is biggish for differences such as size, sizes when use the casting integral shroud of uniform sizes, to re-work lower point of half internal clamping block of cost without hollow single crystal turbine blade is preced with, without the outer fixture block of the higher entirety of multiple processing cost.
Description
Technical field
The present invention relates to aero-engines without hollow single crystal turbine blade blade tip loading method is preced with, in laboratory condition
Lower realize loads to without stablizing for the hollow single crystal turbine blade of hat, and then progress is cut without specific examine of hollow single crystal turbine blade is preced with
The fatique testing at elevated temperature in face belongs to aerospace technical field of engines.
Background technique
Without one of the widely applied core component that hollow single crystal turbine blade is current aerospace engine is preced with, work in height
In warm environment, huge centrifugal force is born, easily generation fatigue rupture.Therefore, carry out without the hollow single crystal turbine blade examination of hat
The fatique testing at elevated temperature in section has a very important significance.
In terms of turbo blade blade tip load, the loading method of different turbo blades is different.It is first for Shrouded turbine blade
It first needs to check intensity of the integral shroud under test load, if integral shroud intensity is enough, tensile load can be born by integral shroud,
Realize the simulation of turbo blade mechanical load；If it is inadequate to be preced with intensity, also need that other modes is taken to transmit centrifugation together with integral shroud
Load, such as friction-loaded.For without hat turbo blade, since the examination section of usual turbo blade is located in turbo blade
Portion can not provide enough grasping parts for friction-loaded, it is difficult to be directly realized by the load of turbo blade blade tip.Aviation Industry of China
Shenyang engine design and research institute, group company using tip segment weld clamping end by the way of loaded (CN
202467935 U), for without hat equiax crystal high-temperature alloy turbine blade, the program is feasible.But for without hat single crystal turbine blade
For, the welding of turbo blade blade tip is operated, will lead to the destruction of turbo blade crystal perfection, and since monocrystalline is without crystalline substance
Boundary's intensified element, fatigue strength, the heat-resisting ability of the high temperature alloy of polycrystalline form will be significantly reduced, be easy during test
It is cracked in commissure first, lead to test failure.In order to solve the potential risk, Beijing Institute of Aeronautics Wang Rongqiao, Jing Fulei etc. are used
At the blade tip position without the hollow single crystal turbine blade of hat in such a way that shorter and smaller special-shaped integral shroud cooperation of casting divides half vane fixture
Loaded (Wang Rongqiao, Jing Fulei, Hu Dianyin single crystal turbine blade thermal mechanical fatigue experimental technique [J] aviation power journal,
2013,28(2):252-258.).Although the integral shroud that casting is formed can be realized the stable holding of integral shroud.However, due to turbine leaf
Piece examines cross-sectional distance fixture closer, and fixture destroys first at high temperature in order to prevent, needs to introduce cooling water to fixture
It is cooled down, not only increases processing cost and the cooling water hole introduced and connection divide the bolt hole of half vane fixture can also
Weaken the integral strength of blade holder；Simultaneously because integral shroud is abnormal shape, different leaves need to process different integral shroud fixtures, cost compared with
It is high.
In conclusion matched clamp processing is multiple currently without hollow single crystal turbine blade blade tip loading method and not perfect is preced with
It is miscellaneous, cost is excessively high, still have larger room for improvement.
Summary of the invention
Technical problem solved by the present invention is providing one kind for without hollow single crystal turbine blade blade tip loading problem is preced with
Processing cost is low, easy to use without hollow single crystal turbine blade blade tip loading method is preced with, for without the hollow single crystal turbine leaf of hat
Piece examines fatigue test of the section in room temperature to 1000 DEG C of temperature ranges of high temperature.
The technical solution of the invention is as follows: before without hollow single crystal turbine blade casting is preced with, welding one on its wax-pattern
A integral shroud wax-pattern forms combination wax-pattern, then utilizes the combination lost wax casting shrouded blade testpieces, and this method makes band
The casting integral shroud part of shroud blade testpieces and single crystal state is kept without hollow single crystal turbine blade part is preced with, ensure that casting
Make integral shroud and the intensity without hat hollow single crystal turbine blade blade tip junction.Casting integral shroud is inverted ladder-shaped body structure, internal band
The airflow channel that cooling air-flow is smoothly discharged inside guaranteed hollow single crystal turbine blade；The length of integral shroud is cast by hollow without being preced with
Single crystal turbine blade examines section to determine at a distance from without the hollow single crystal turbine blade blade tip of hat, if without hollow single crystal turbine leaf is preced with
Piece examination section can be made by changing casting integral shroud length without the hollow monocrystalline whirlpool of hat close to without hollow single crystal turbine blade blade tip is preced with
The distance of 5cm-10cm is arranged at impeller blade examination cross-sectional distance special fixture bottom, can prevent special fixture in examination section in this way
It is heated during heating, special fixture intensity is influenced, while the Cooling Design of special fixture can be saved and reduce processing cost.
The casting integral shroud of shrouded blade testpieces is connect with point half internal clamping block for designed special fixture, by designed exclusive clamps
Tool may be implemented without the hollow single crystal turbine blade blade tip load of hat.Special fixture is made of point half internal clamping block and whole outer fixture block,
Divide half internal clamping block and cast the inverted ladder-shaped body cavity that can be packed into just in the middle part of whole outer fixture block after integral shroud cooperates, for size, greatly
The differences such as small are biggish without hollow single crystal turbine blade is preced with, and when can not use the casting integral shroud of uniform sizes, re-work cost
Lower point of half internal clamping block, without the outer fixture block of the higher entirety of multiple processing cost.It is hollow without being preced under practical service condition
The whole of single crystal turbine blade bears tensile load, and special fixture can satisfy tensile loads demand.
The advantages of the present invention over the prior art are that: the present invention can be realized without the hollow single crystal turbine blade blade tip of hat
Stable holding in fatique testing at elevated temperature can be used for without the hollow specific examination section of single crystal turbine blade of hat in room temperature to high temperature
Fatigue test within the temperature range of 1200 DEG C, without considering that fixture is cooling and is bolted bring special fixture intensity not
The problem of foot, processing cost is low, and assembly is simple, easy to use.
Detailed description of the invention
Fig. 1 is without the hollow single crystal turbine blade schematic diagram of hat, wherein (a) is blade back figure；It (b) is leaf basin figure；B is blade tip；C
For blade；D is listrium；E is to stretch root；F is tenon；
Fig. 2 is shrouded blade testpieces schematic diagram, wherein A be casting integral shroud, C be blade, D is listrium, E be stretch root, F is
Tenon；
Fig. 3 is a point half internal clamping block schematic diagram, wherein (a) is outside drawing；It (b) is front view；It (c) is left view；It (d) is to bow
View；
Fig. 4 is whole outer fixture block schematic diagram, wherein (a) is outside drawing；It (b) is front view；It (c) is top view；It (d) is a left side
View；
Fig. 5 is assembling schematic diagram；
Specific embodiment
Fig. 1 is without the hollow single crystal turbine blade schematic diagram of hat, and wherein B is blade tip, C is blade, D is listrium, E is to stretch root, F
It needs to realize without the hollow single crystal turbine blade of hat for the examination for realizing turbo blade dangerouse cross-section under laboratory condition for tenon
Blade tip stablizes load.
The present invention is a kind of without hollow single crystal turbine blade blade tip loading method is preced with, and specific embodiment is as follows:
(1) before without hollow single crystal turbine blade casting is preced with, an integral shroud wax-pattern is welded on its wax-pattern, forms combination wax
Then mould utilizes the combination lost wax casting shrouded blade testpieces, as shown in Fig. 2, wherein A is casting integral shroud, C is blade, D
For listrium, E be stretch root, F is tenon, this method makes the casting integral shroud part of shrouded blade testpieces and without being preced with hollow monocrystalline
Turbine vane segment keeps single crystal state, ensure that casting integral shroud and without hat hollow single crystal turbine blade blade tip junction
Intensity.Casting integral shroud is inverted ladder-shaped body structure, inside smoothly arranged with cooling air-flow inside guaranteed hollow single crystal turbine blade
Airflow channel out；The length of integral shroud is cast by without the hollow single crystal turbine blade examination section of hat and without the hollow single crystal turbine leaf of hat
The distance of piece blade tip determines, if without hollow single crystal turbine blade examination section is preced with close to without being preced with hollow single crystal turbine blade blade tip,
It can make to examine cross-sectional distance special fixture bottom to have 5cm- without the hollow single crystal turbine blade of hat by changing casting integral shroud length
The distance of 10cm can prevent special fixture heated during examining section to heat in this way, influence special fixture intensity, simultaneously
The Cooling Design of special fixture can be saved and reduce processing cost.
(2) it realizes without the hollow single crystal turbine blade blade tip load of hat also by designed special fixture, such as Fig. 3,4 institutes
Show, special fixture is made of point half internal clamping block 3 and whole outer fixture block 4, the casting leaf of shrouded blade testpieces 2 (as shown in Figure 2)
It is preced with and is connect with point half internal clamping block 3 (as shown in Figure 3) for designed special fixture, point half internal clamping block 3 (as shown in Figure 3) and casting
The inverted ladder-shaped body cavity that can be packed into just in the middle part of whole outer fixture block 4 (as shown in Figure 4) after integral shroud cooperation, assembles result such as Fig. 5 institute
Show, wherein 2 be shrouded blade testpieces, 3 be point half internal clamping block, 4 be whole outer fixture block.
Due to bearing tensile load in the actual process without the hollow single crystal turbine blade of hat, in laboratory conditions
When to testing without hat hollow single crystal turbine blade examination section, also apply the tensile load of alternation, at this point, in the present invention
Special fixture can satisfy load needs, for different without hollow single crystal turbine blade is preced with, use external dimensions identical as far as possible
Integral shroud (internal cooling channel can be different) are cast, without repeatedly half internal clamping block of processing point and whole outer fixture block, reduction is processed into
This；It, can not be using (the inside cooling of the identical casting integral shroud of external dimensions for differing greatly without hollow single crystal turbine blade is preced with
Channel can be different) in the case where, point half internal clamping block accordingly is re-worked, the higher entirety of multiple processing cost is not necessarily to
Outer fixture block reduces processing cost.
Claims (1)
1. a kind of without the hollow single crystal turbine blade blade tip loading method of hat, it is characterised in that: without the hollow single crystal turbine blade of hat
Before casting, an integral shroud wax-pattern is welded on its wax-pattern, is formed combination wax-pattern, is then preced with leaf using the combination lost wax casting band
Piece testpieces, the casting integral shroud part of shrouded blade testpieces and keeps single lenticular without hollow single crystal turbine blade part is preced with
State ensure that casting integral shroud and the intensity without hat hollow single crystal turbine blade blade tip junction；The casting of shrouded blade testpieces
Integral shroud is connect with point half internal clamping block for designed special fixture, the whole outer clip of point half internal clamping block and designed special fixture
Block connection may be implemented to load without the hollow single crystal turbine blade blade tip of hat by designed special fixture；
The special fixture is made of point half internal clamping block and whole outer fixture block, is filled just after point half internal clamping block and casting integral shroud cooperation
Enter the inverted ladder-shaped body cavity in the middle part of whole outer fixture block, it is biggish without the hollow single crystal turbine blade of hat, nothing for size, difference in size
When method uses the casting integral shroud of uniform sizes, lower point of half internal clamping block of cost is re-worked, is not necessarily to multiple processing cost
The outer fixture block of higher entirety；
The casting integral shroud is inverted ladder-shaped body structure, internal smoothly to arrange with cooling air-flow inside guaranteed hollow single crystal turbine blade
Airflow channel out；Integral shroud is cast along the length in inverted ladder-shaped body structure height direction by cutting without the hollow single crystal turbine blade examination of hat
Face determines at a distance from without the hollow single crystal turbine blade blade tip of hat, if without hollow single crystal turbine blade examination section is preced with close to no hat
Hollow single crystal turbine blade blade tip is made by changing length of the casting integral shroud along inverted ladder-shaped body structure height direction without the hollow list of hat
The distance of 5cm-10cm is arranged at brilliant turbo blade examination cross-sectional distance special fixture bottom, prevents special fixture from heating in examination section
It is heated in the process, influences special fixture intensity, while saving the Cooling Design of special fixture.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810283505.1A CN108547667B (en) | 2018-04-02 | 2018-04-02 | It is a kind of without being preced with hollow single crystal turbine blade blade tip loading method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810283505.1A CN108547667B (en) | 2018-04-02 | 2018-04-02 | It is a kind of without being preced with hollow single crystal turbine blade blade tip loading method |
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| Publication Number | Publication Date |
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| CN108547667A CN108547667A (en) | 2018-09-18 |
| CN108547667B true CN108547667B (en) | 2019-04-16 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114718655B (en) * | 2022-04-02 | 2023-08-04 | 浙江大学 | Non-uniform structure single crystal turbine blade and preparation method thereof |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2985582A1 (en) * | 2014-08-13 | 2016-02-17 | Siemens Aktiengesellschaft | Test device and test method for determining a material fatigue and blade claw test body |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3802255A (en) * | 1972-03-08 | 1974-04-09 | Us Air Force | Fixture for tensile and stress rupture testing of turbine blades |
| US7549345B2 (en) * | 2004-06-14 | 2009-06-23 | Surface Technology Holdings, Ltd. | Method and apparatus for sensing distortion |
| CN202467935U (en) * | 2011-12-21 | 2012-10-03 | 中国航空工业集团公司沈阳发动机设计研究所 | Blade tip loading structure for turbine blade |
| WO2016060417A1 (en) * | 2014-10-17 | 2016-04-21 | 한국기계연구원 | Fairing, and fatigue test apparatus and method using same |
| CN204988102U (en) * | 2015-09-28 | 2016-01-20 | 成都弘佛科技有限公司 | Blade comprehensive testing device |
| KR101807589B1 (en) * | 2016-02-05 | 2018-01-18 | 두산중공업 주식회사 | Fatigue testing machine for measuring fatigue of the connection of the blades and the rotor disc specimen sample. |
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2018
- 2018-04-02 CN CN201810283505.1A patent/CN108547667B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2985582A1 (en) * | 2014-08-13 | 2016-02-17 | Siemens Aktiengesellschaft | Test device and test method for determining a material fatigue and blade claw test body |
Non-Patent Citations (1)
| Title |
|---|
| Thermomechanical fatigue failure investigation on a single crystal nickel superalloy turbine blade;Rongqiao Wang etc.;《Engineering Failure Analysis》;20160815;第284-295页 |
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