CN206513406U - A kind of High Pressure Turbine Rotor blade and the engine with it - Google Patents
A kind of High Pressure Turbine Rotor blade and the engine with it Download PDFInfo
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- CN206513406U CN206513406U CN201720084202.8U CN201720084202U CN206513406U CN 206513406 U CN206513406 U CN 206513406U CN 201720084202 U CN201720084202 U CN 201720084202U CN 206513406 U CN206513406 U CN 206513406U
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- anticollision
- high pressure
- turbine rotor
- pressure turbine
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Abstract
The utility model discloses a kind of High Pressure Turbine Rotor blade and the engine with it, it is related to technical field of engines.The High Pressure Turbine Rotor blade (1) is provided with anticollision breach (11) at the trailing edge of blade tip, the anticollision breach (11) includes the first anticollision face (12), and the first anticollision face (12) is less than size of the blade tip in blade (1) short transverse in the size of blade (1) short transverse.The engine includes High Pressure Turbine Rotor blade as described above.The utility model has the advantage of：High Pressure Turbine Rotor blade of the present utility model is provided with anticollision breach at the trailing edge of blade tip, the contact-impact because of deformable blade and stator casing can be avoided, it is effectively reduced that blade tip is non-homogeneous to touch mill intensity, blade tip is avoided to cause large area arrisdefect because touching mill and then injure other blades, add the reliability of blade, the application risk and maintenance cost of blade and engine are reduced, with huge economic benefit.
Description
Technical field
The utility model is related to technical field of engines, and in particular to a kind of High Pressure Turbine Rotor blade and the hair with it
Motivation.
Background technology
Gas-turbine unit generally comprises compressor, combustion chamber and the big part of turbine three.It is high by the high temperature of combustion chamber
Compression ignition air-flow is after nozzle ring, and flow expansion accelerates, then impulse turbine rotor blade, drives turbine rotor rotation, will
The heat of combustion gas is dynamic and kinetic energy is converted into mechanical energy.For axial flow type gas turbogenerator, there are complicated three in turbine cascade
Dimension flowing, due to there is gap, and the pressure of rotor blade between the blade tip and static turbine casing component of rotor blade
There is larger pressure difference in face and suction surface, cause blade tip to there is obvious gas leakage, and above-mentioned phenomenon can influence the effect of engine
Rate.Turbine rotor needs operationally to keep suitable tip clearance, is unlikely to cause rotor and turbine because gap is too small
Casket occurs excessively to touch mill；Larger tip leakage and performance loss can not be brought because gap is excessive.
Typical High Pressure Turbine Rotor blade tip has band crown structure and without crown structure, wherein band hat structure can be with
The blade tip leakage loss of blade is reduced, plays a part of damping, and improves the fatigue strength of blade, but on the other hand, band hat
Blade needs more cold air to go to cool down blade tip, adds the centrifugal load of blade and the turbine disk, and increases manufacturing expense, because
This, applies more extensive without crown structure on High Pressure Turbine Rotor blade.Turbo blade blade tip and static turbine casing
, it is necessary to keep necessary gap during cooperation.In engine production, its processing has been made decision with assembly precision original state, and its is cold
State tip clearance, but in use, engine is in different working conditions, particularly in transient state, such as takes off, subtracts
Speed, further accelerate and the operating point such as land, the tip clearance of engine rotor also changes therewith, it is possible to touch mill feelings
Condition.
Generally, High Pressure Turbine Rotor blade is used without crown structure, and the blade tip of High Pressure Turbine Rotor blade is with solid
Determine diameter design, and the turbine casing component of annular coordinates, to ensure engine performance, gap very little between the two, blade tip
Each region is identical with the gap of turbine casing component.This structure has certain application risk, in the operating condition, turbine part quilt
High-temperature fuel gas is heated, but is due to that turbine rotor where turbine rotor blade is very fast by the speed of rotatable elongate, and static element
Speed such as turbine casing expanded by heating is slower, and both thermal deformations exist uncoordinated.Without the High Pressure Turbine Rotor blade of hat, bag
Include in leading edge, leaf and each region such as trailing edge it is heated after the Temperature Distribution that shows and uneven, it is however generally that, leading edge and trailing edge
Temperature is higher, and such leading edge and trailing edge expanded by heating are more severe, adds the effect of centrifugal force so that blade and the turbine disk are stretched rapidly
It is long, therefore when instantaneous working point such as takes off, turbine blade clearance reduces rapidly, or even can occur blade tip and turbine casing component
Touch mill phenomenon.Because each position elongation of blade tip is variant, this mill that touches is uneven, and the blade tip stress shape when touching mill
Condition very severe, therefore at the weaker trailing edge blade tip of structure, may occur arrisdefect event because of this non-homogeneous mill that touches
Hinder, and arrisdefect is possible to injure other blades, brings economic loss and potential safety hazard.
Utility model content
The purpose of this utility model is to provide a kind of High Pressure Turbine Rotor blade and the engine with it, with solution or extremely
Less at least one in the presence of mitigation background technology the problem of.
The technical solution adopted in the utility model is：A kind of High Pressure Turbine Rotor blade, trailing edge of the blade in blade tip are provided
Place is provided with anticollision breach, and the anticollision breach includes the first anticollision face, and the first anticollision face is in blade height
The size in direction is less than size of the blade tip in blade height direction.
Preferably, the anticollision breach also includes transition circle cambered surface, and the two ends of the transition circle cambered surface connect institute respectively
State the first anticollision face and blade tip.
Preferably, connected between the blade tip and the first anticollision face by the first inclined plane, described first tilts
Angle between face and the first anticollision face is more than 90 degree, the connection in first inclined plane and the first anticollision face
Locate round-corner transition, first inclined plane and the junction round-corner transition of the blade tip.
Preferably, compensating groove, leaf basin of the compensating groove from blade are provided between the first anticollision face and blade tip
Extend to blade back, the size of the bottom surface of the compensating groove in blade height direction is less than the first anticollision face in blade height
The size in direction.
Preferably, the blade is internally provided with cavity, and the cavity is used to be passed through the table that high pressure cold cools down blade
Face temperature.
Preferably, the trailing edge of the blade is provided with cooling and splits seam, and the cooling is split seam and is arranged on the leaf pelvic surface of sacrum of trailing edge,
For the cold air in the cavity to be drained into trailing edge surface.
The utility model additionally provides a kind of engine, and the engine includes High Pressure Turbine Rotor leaf as described above
Piece.
The beneficial effects of the utility model are：
High Pressure Turbine Rotor blade of the present utility model is provided with anticollision breach at the trailing edge of blade tip, can avoid because
The contact-impact of deformable blade and stator casing, is effectively reduced that blade tip is non-homogeneous to touch mill intensity, it is to avoid blade tip is led because touching mill
Cause large area arrisdefect and then injure other blades, add the reliability of blade, reduce the application risk of blade and engine
And maintenance cost, with huge economic benefit.
Brief description of the drawings
Fig. 1 is the schematic diagram of the High Pressure Turbine Rotor blade of the embodiment of the utility model one.
Fig. 2 is the schematic cross-section of blade shown in Fig. 1.
Wherein, 1- blades, 11- anticollision breach, the first anticollisions of 12- face, 13- transition circle cambered surfaces, 14- cavitys, 2- leaves
Point, 3- trailing edges, 4- leaf basins, 5- blade backs, 6- leading edges.
Embodiment
To make the purpose, technical scheme and advantage of the utility model implementation clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, the technical scheme in the utility model embodiment is further described in more detail.In the accompanying drawings, from beginning
Same or similar element or element with same or like function are represented to same or similar label eventually.Described reality
It is a part of embodiment of the utility model to apply example, rather than whole embodiments.The embodiment described below with reference to accompanying drawing
It is exemplary, it is intended to for explaining the utility model, and it is not intended that to limitation of the present utility model.It is new based on this practicality
Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained under the premise of creative work is not made
Example, belongs to the scope of the utility model protection.Embodiment of the present utility model is described in detail below in conjunction with the accompanying drawings.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, is for only for ease of description the utility model and simplifies description, rather than indicate or imply and be signified
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The limitation of novel protected scope.
As shown in Figure 1 and Figure 2, a kind of High Pressure Turbine Rotor blade, includes blade tip 2, trailing edge 3, leaf basin 4 and blade back 5, blade 1
Anticollision breach 11 is provided with the trailing edge 3 of blade tip, anticollision breach 11 includes the first anticollision face 12, the first anticollision face
12 the short transverse of blade 1 size be less than blade tip the short transverse of blade 1 size.The short transverse refers to from blade 1
Blade root to the direction of blade tip.
Because blade 1 is provided with anticollision breach 11 at the trailing edge of blade tip, when blade 1 is heated by high-temperature fuel gas
Afterwards, occur by thermalizing collision, add the effect of rotor centrifugal force so that blade and turbine disk elongation, particularly the blade tip tail of blade 1
At edge, because trailing edge 3 is relatively thin, dilatancy is larger, by setting anticollision breach 11 to prevent the trailing edge and stator of blade tip 2
Casing collides, it is to avoid because of the contact-impact of deformable blade and stator casing, is effectively reduced that blade tip is non-homogeneous to touch mill intensity,
Avoid blade tip from causing large area arrisdefect because touching mill and then injure other blades, add the reliability of blade, reduce blade
With the application risk and maintenance cost of engine, with huge economic benefit.
In the present embodiment, anticollision breach 11 also includes transition circle cambered surface 13, and the two ends of transition circle cambered surface 13 connect respectively
Connect the first anticollision face 12 and blade tip 2.It the advantage is that, by arc surface transition, the locally generation stress of blade tip 2 can be prevented
Concentrate, particularly the junction of blade tip 1 and anticollision breach 11.
It is understood that the connection between blade tip 2 and anticollision breach 11 can also take other form.For example,
In one alternative, between the anticollision face 12 of blade tip 2 and first by the first inclined plane connect, first inclined plane with
Angle between first anticollision face 12 is 150 degree, first inclined plane and the junction fillet mistake in the first anticollision face 12
Cross, first inclined plane and the junction round-corner transition of blade tip 2.The first anticollision face 12 is connected by using the first inclined plane
And blade tip 2, and round-corner transition is set at the two ends of the first inclined plane, it can equally play a part of reducing stress concentration.
Can immediately, the angle between first inclined plane and the first anticollision face 12 can also be according to actual feelings
Condition is set, as long as the angle met between first inclined plane and the first anticollision face 12 is more than 90 degree.
In another alternative embodiment, be provided with compensating groove between the first anticollision face 12 and blade tip 2, the compensating groove from
The leaf basin 4 of blade 1 extends to blade back 5, and the size of the bottom surface of the compensating groove in blade height direction is less than the first anticollision face
12 blade height direction size.Using compensating groove, it can equally play a part of preventing stress concentration.
In the present embodiment, blade 1 is internally provided with cavity 14, and cavity is with 14 in being passed through high pressure cold cooling blade
Surface temperature.It is understood that the inside of cavity 14 can also set water conservancy diversion rib, to realize the flowing of high pressure cold, prevent
Cooling dead angle is produced, is conducive to improving cooling effect.
It is understood that the cooling in order to preferably realize blade trailing edge 3, can also set cold in the trailing edge of blade 1
But seam is split, the cooling is split seam and is arranged on the leaf pelvic surface of sacrum of trailing edge, for the cold air in cavity 14 to be drained into trailing edge surface, shape
Into cooling air film, trailing edge surface is separated with high-temperature fuel gas.
It is understood that it is different according to the degrees of expansion of different model rotor blade, can be to the first anticollision face 12
Size and size difference of the blade tip in blade height direction in blade height direction optimize design, lack while optimizing anticollision
Mouth 11 is from blade inlet edge 6 to the width dimensions in the direction of trailing edge 3, it is to avoid because the design of anticollision breach 11 brings extra performance to damage
Lose.
The utility model additionally provides a kind of engine, and the engine includes High Pressure Turbine Rotor leaf as described above
Piece.It is reduction High Pressure Turbine Rotor blade, especially relatively weak by setting anticollision breach at the blade tip trailing edge of blade
Trailing edge blade tip position and turbine casing component touch mill intensity, it is to avoid because the non-homogeneous mill that touches causes blade tip arrisdefect.To high-pressure turbine
Rotor blade carries out the local top rake of blade tip, because top rake region is smaller, the height also very little, therefore will not bring extra of top rake
Performance loss, it is ensured that the performance of engine.
It is last it is to be noted that：Above example is only limited to illustrate the technical solution of the utility model, rather than to it
System.Although the utility model is described in detail with reference to the foregoing embodiments, one of ordinary skill in the art should manage
Solution：It can still be modified to the technical scheme described in foregoing embodiments, or which part technical characteristic is entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from each embodiment of the utility model
The spirit and scope of technical scheme.
Claims (7)
1. a kind of High Pressure Turbine Rotor blade, it is characterised in that：
Blade (1) is provided with anticollision breach (11) at the trailing edge of blade tip, and the anticollision breach (11) includes the first anti-collision
Face (12) is hit, the first anticollision face (12) is less than the blade tip in blade (1) height in the size of blade (1) short transverse
The size in direction.
2. High Pressure Turbine Rotor blade as claimed in claim 1, it is characterised in that：The anticollision breach (11) also included
Arc surface (13) is crossed, the two ends of the transition circle cambered surface (13) connect the first anticollision face (12) and blade tip respectively.
3. High Pressure Turbine Rotor blade as claimed in claim 1, it is characterised in that：The blade tip and the first anticollision face
(12) connected between by the first inclined plane, the angle between first inclined plane and the first anticollision face (12) is more than
90 degree, the junction round-corner transition of first inclined plane and the first anticollision face (12), first inclined plane and institute
State the junction round-corner transition of blade tip.
4. High Pressure Turbine Rotor blade as claimed in claim 1, it is characterised in that：The first anticollision face (12) and blade tip
Between be provided with compensating groove, the compensating groove extends to blade back from the leaf basin of blade, and the bottom surface of the compensating groove is in blade height
The size in direction is less than size of the first anticollision face (12) in blade height direction.
5. the High Pressure Turbine Rotor blade as described in any one of Claims 1-4, it is characterised in that：The inside of the blade (1)
Cavity is provided with, the cavity is used to be passed through the surface temperature that high pressure cold cools down blade.
6. High Pressure Turbine Rotor blade as claimed in claim 5, it is characterised in that：The trailing edge of the blade (1) is provided with cold
But seam is split, the cooling is split seam and is arranged on the leaf pelvic surface of sacrum of trailing edge, for the cold air in the cavity to be drained into trailing edge surface.
7. a kind of engine, it is characterised in that：The engine includes High Pressure Turbine Rotor blade as claimed in claim 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720084202.8U CN206513406U (en) | 2017-01-23 | 2017-01-23 | A kind of High Pressure Turbine Rotor blade and the engine with it |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720084202.8U CN206513406U (en) | 2017-01-23 | 2017-01-23 | A kind of High Pressure Turbine Rotor blade and the engine with it |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206513406U true CN206513406U (en) | 2017-09-22 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720084202.8U Active CN206513406U (en) | 2017-01-23 | 2017-01-23 | A kind of High Pressure Turbine Rotor blade and the engine with it |
Country Status (1)
| Country | Link |
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| CN (1) | CN206513406U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112554960A (en) * | 2020-12-02 | 2021-03-26 | 中国航发沈阳发动机研究所 | Turbine rotor blade apex structure and have its turbine rotor |
-
2017
- 2017-01-23 CN CN201720084202.8U patent/CN206513406U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112554960A (en) * | 2020-12-02 | 2021-03-26 | 中国航发沈阳发动机研究所 | Turbine rotor blade apex structure and have its turbine rotor |
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