CN205936702U - High pressure turbine rotor - Google Patents
High pressure turbine rotor Download PDFInfo
- Publication number
- CN205936702U CN205936702U CN201620876709.2U CN201620876709U CN205936702U CN 205936702 U CN205936702 U CN 205936702U CN 201620876709 U CN201620876709 U CN 201620876709U CN 205936702 U CN205936702 U CN 205936702U
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- pressure turbine
- high pressure
- turbine rotor
- blade
- utility
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Abstract
The utility model relates to an aeroengine structure designs field, in particular to high pressure turbine rotor to solve current hole and visit the unable problem of judging apex wearing and tearing volume size of inspection method. High pressure turbine rotor includes a plurality of blades, partly the apex outer fringe department of blade sets up the opening of two at least opening little -endians. The utility model discloses a high pressure turbine rotor can pass through to detect the opening depth change condition in order to judge the apex wearing and tearing condition, the in -process blade that prevents to take a trial run emergence excessive wear, the safety that the assurance blade uses and the complete machine is taken a trial run, simultaneously, can provide the reference for engine vibration, performance analysis etc..
Description
Technical field
This utility model is related to aero-engine field of structural design, particularly to a kind of High Pressure Turbine Rotor.
Background technology
Shown in existing high-pressure turbine structure diagram reference Fig. 1, including outer shroud block 4 and turbo blade；In high-pressure turbine work
When making, the factor such as can mismatch due to the creep elongation of itself and with the thermal expansion of outer interannular so that blade 3 and outer shroud block 4
Mill is touched in life.If blade tip serious wear may lead to blade top cover 2 to fly out, low pressure blade of injuring；Meanwhile, cold air can be from top cover 2
Position is revealed in a large number, leads to blade to lack cold air and ablation occurs, bring serious potential safety hazard to whole machine test run.
Therefore, the judgement to the blade tip degree of wear is particularly important.Reviewing party is visited using the whole machine state lower opening being currently known
Method, though can determine whether whether the blade tip of blade weares and teares, because blade surface is smooth surface, lack object of reference, so being difficult to
Judge wear extent size.
Content of the invention
The purpose of this utility model there is provided a kind of High Pressure Turbine Rotor, cannot be sentenced with solving existing hole spy inspection method
The problem of disconnected blade tip wear extent size.
The technical solution of the utility model is：
A kind of High Pressure Turbine Rotor, including multiple blades, offers at least at the blade tip outer rim of a part of described blade
The ascending gap of two openings.
Preferably, described gap includes 3.
Preferably, the depth of 3 described gap is respectively 0.25mm, 0.50mm and 0.75mm.
Preferably, described gap semicircular in shape.
Preferably, the blade with described gap is 4, and adjacent angle between blade described in two panels is 90 °.
The utility model has the advantage of：
High Pressure Turbine Rotor of the present utility model, can judge blade tip abrasion feelings by detecting gap change in depth situation
Condition, prevents commissioning process Leaf from excessive wear occurring it is ensured that blade uses and whole machine test run safety；Meanwhile, can shake for whole machine
Dynamic, performance evaluation etc. provides reference.
Brief description
Fig. 1 is the structure schematic diagram of existing High Pressure Turbine Rotor；
Fig. 2 is the structural representation of this utility model High Pressure Turbine Rotor blade；
Fig. 3 is the sectional view of this utility model High Pressure Turbine Rotor blade.
Specific embodiment
For making purpose, technical scheme and advantage that this utility model is implemented clearer, below in conjunction with this utility model
Accompanying drawing in embodiment, is further described in more detail to the technical scheme in this utility model embodiment.In the accompanying drawings, ad initio
To the element that same or similar label represents same or similar element or has same or like function eventually.Described reality
Applying example is a part of embodiment of this utility model, rather than whole embodiments.Embodiment below with reference to Description of Drawings
It is exemplary it is intended to be used for explaining this utility model, and it is not intended that to restriction of the present utility model.New based on this practicality
Embodiment in type, the every other enforcement that those of ordinary skill in the art are obtained under the premise of not making creative work
Example, broadly falls into the scope of this utility model protection.Below in conjunction with the accompanying drawings embodiment of the present utility model is described in detail.
In description of the present utility model it is to be understood that term " " center ", " longitudinal ", " horizontal ", "front", "rear",
The orientation of instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outward " or position relationship are based on accompanying drawing institute
The orientation showing or position relationship, are for only for ease of description this utility model and simplify description, rather than instruction or hint indication
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The restriction of novel protected scope.
1- Fig. 3 is described in further details to this utility model High Pressure Turbine Rotor below in conjunction with the accompanying drawings.
This utility model provides a kind of High Pressure Turbine Rotor, including multiple blades 3, in the leaf of a part of described blade 3
The ascending gap of at least two openings 31 is offered at sharp outer rim.
Wherein, the quantity of gap 31, size and shape can carry out suitable setting as needed, excellent in the present embodiment
Gap 31 is selected to include 3；The depth of 3 gap 31 is respectively 0.25mm, 0.50mm and 0.75mm；Further, gap 31 is in half
Circular.
Equally, the quantity of the blade 3 of setting gap 31 can also carry out suitable selection as needed；In the present embodiment,
The blade 3 with gap 31 is 4, and the angle between adjacent two panels blade 3 is 90 °, adds deviation from circular from pair to reduce machine
The impact of blade tip length.
This utility model provides in High Pressure Turbine Rotor, in order to be able to realize the having of abrasion condition of blade tip in whole machine state
Effect monitoring, using blade tip as object of reference, blade tip open radius different semicircle gap 31, permissible when blade tip occurs to wear and tear
Blade tip wear extent is judged by the situation of change observing gap 31 depth, according to designer, blade tip can be worn and torn in practical application
The depth to adjust gap 31 for the requirement of amount；Need the strict size controlling gap 31 to slit with carrying to reduce performance loss simultaneously
The quantity of mouth blade 3.
The above, specific embodiment only of the present utility model, but protection domain of the present utility model does not limit to
In this, any those familiar with the art in the technical scope that this utility model discloses, the change that can readily occur in
Change or replace, all should cover within protection domain of the present utility model.Therefore, protection domain of the present utility model should be with described
Scope of the claims is defined.
Claims (5)
1. a kind of High Pressure Turbine Rotor, including multiple blades (3) it is characterised in that outside the blade tip of a part of described blade (3)
The ascending gap of at least two openings (31) are offered at edge.
2. High Pressure Turbine Rotor according to claim 1 is it is characterised in that described gap (31) includes 3.
3. High Pressure Turbine Rotor according to claim 2 is it is characterised in that the depth of 3 described gap (31) is respectively
0.25mm, 0.50mm and 0.75mm.
4. the High Pressure Turbine Rotor according to any one of claim 1-3 is it is characterised in that described gap (31) is in semicircle
Shape.
5. High Pressure Turbine Rotor according to claim 4 is it is characterised in that the blade (3) with described gap (31) is 4
Piece, and adjacent angle between blade (3) described in two panels is 90 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620876709.2U CN205936702U (en) | 2016-08-12 | 2016-08-12 | High pressure turbine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620876709.2U CN205936702U (en) | 2016-08-12 | 2016-08-12 | High pressure turbine rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205936702U true CN205936702U (en) | 2017-02-08 |
Family
ID=57921041
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620876709.2U Active CN205936702U (en) | 2016-08-12 | 2016-08-12 | High pressure turbine rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205936702U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110877234A (en) * | 2019-11-26 | 2020-03-13 | 中国航发沈阳黎明航空发动机有限责任公司 | Outer ring block grinding method capable of realizing automatic eccentric grinding and on-machine measurement |
-
2016
- 2016-08-12 CN CN201620876709.2U patent/CN205936702U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110877234A (en) * | 2019-11-26 | 2020-03-13 | 中国航发沈阳黎明航空发动机有限责任公司 | Outer ring block grinding method capable of realizing automatic eccentric grinding and on-machine measurement |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |