CN208546354U - Axial flow compressor and its rotor hub zigzag listrium - Google Patents
Axial flow compressor and its rotor hub zigzag listrium Download PDFInfo
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- CN208546354U CN208546354U CN201820619654.6U CN201820619654U CN208546354U CN 208546354 U CN208546354 U CN 208546354U CN 201820619654 U CN201820619654 U CN 201820619654U CN 208546354 U CN208546354 U CN 208546354U
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Abstract
The purpose of this utility model is to provide a kind of axial flow compressor and its rotor hub zigzag listriums, can reduce the caused aerodynamic loss of leakage between grade.One of axial flow compressor rotor root zigzag listrium, including the rotor listrium between adjacent rotor blades, multiple grooves that the setting indention suction surface of the rotor blade pressure face to another rotor blade on the rotor listrium is circumferential from the adjacent rotor blades is distributed, the multiple depth of groove is gradually changed in the form of conic section along axial direction, and reaches maximum in the outlet side of the rotor listrium.
Description
Technical field
The utility model relates to axial flow compressor rotor listriums.
Background technique
In multi stage axial flow compressor operating, due to operating condition changes or is other, axial flow compressor rotation will lead to
Component, i.e. axial force suffered by rotor change, so that will lead to axial flow compressor rotor occurs vibration in the axial direction.Cause
This is needed between rotor structure and stator structure to be avoided high-speed rotating rotor and adjacent stator structure from touching mill
Retain certain axial distance, so as to form the axial gap between rotor disk and stator inner flow passage structure, i.e., between grade between
Gap.Under usual situation, is leaked between grade to reduce, labyrinth gas seals structure is used between rotor drum and stator integral shroud inner wall.
But the requirement with compressor to performance, grade pressure ratio become higher and higher, cause stator leaf row import/export it
Between pressure difference it is higher and higher, thus between grade can be made leakage be difficult to be obturaged completely.It was recognized by the inventor that as shown in Figure 1, arrow
Leakage flow is often returned among sprue with the direction for approaching vertical mainstream between the grade that A1 is indicated, is sent out with arrow A3 upstream incoming flow
Raw blending causes biggish stagnation pressure to lose to can cause biggish loss in root.For high-performance multistage pressure compressor
Later stages, this is often one of main source of flow losses.The low energy fluid of another aspect dilution zone can take the lead in causing fluid
Stall reduces compressor surge nargin.Therefore, it is necessary to a kind of preferable listrium design forms of structure type, to reduce as far as possible
The region that boundary-layer and leakage stream blending occur, and then promote compressor efficiency and surge margin.
Utility model content
The purpose of this utility model is to provide a kind of axial flow compressor and its rotor hub zigzag listriums, can reduce
Aerodynamic loss caused by being leaked between grade.
According to a kind of axial flow compressor rotor root zigzag listrium of the utility model one side, it is included in adjacent rotor
Rotor listrium between blade, wherein from a rotor blade of the adjacent rotor blades on the rotor listrium is circumferential
Multiple grooves that pressure face is distributed to the setting indention between the suction surface of another rotor blade, the multiple depth of groove
It is gradually changed in the form of conic section along axial direction, and reaches maximum in the outlet side of the rotor listrium.
A kind of axial flow compressor according to the utility model another aspect includes a series of alternately arranged stators and rotor,
Rotor is fixed on drum barrel axis, and stator is fixed on casing, and the rotor blade root of rotor passes through rotor listrium and drum barrel axis phase
Even, wherein from a rotor blade pressure face of adjacent rotor blades to another rotor blade on the rotor listrium is circumferential
Suction surface between setting indention be distributed multiple grooves, the multiple depth of groove is along axial direction in the form of conic section
It gradually changes, and reaches maximum in the outlet side of the rotor listrium.
In one or more embodiments, the starting point of the groove is located at the straight line that rotor blade leading edge point is linked to be
On, depth of groove is 0 at start position.
In one or more embodiments, the depth of groove is no more than 1/2 listrium thickness, and depth of groove and grade
Between air flow boundary layer thickness it is suitable.
In one or more embodiments, the point that rotor listrium intersects with rotor blade root is in zigzag most
High point position, all zigzag wave peak positions are on same inner flow passage type face, and zigzag wave trough position is in groove most bottom
End.
In one or more embodiments, along flow direction along, depth of groove from start position to terminal position with secondary song
Line form gradual change, and it is relatively slow in front half section variation, it is very fast in second half section variation.
The beneficial effects of the utility model are:
Labyrinth gas seals structure leaks between being difficult to completely inhibit grade, and this typical forms of Inter-stage gap make because quiet
Sub- front and back pressure difference and leakage stream between the grade that generates, blending can occur with mainstream cause biggish loss, and the utility model passes through more
A depth of groove is gradually changed in the form of conic section along axial direction, and reaches maximum in the outlet side of the rotor listrium, so that
The boundary layer thickness of compressor inner flow passage end wall is obviously reduced, and leakage stream blending region obviously becomes smaller between boundary-layer and grade, pneumatically
Loss reduces, and improves compressor efficiency and surge margin.
Detailed description of the invention
The above and other feature, property and advantage of the utility model will be by with reference to the accompanying drawings and examples
Description and become readily apparent from, in which:
Fig. 1 is interstitial structure and its leakage flow schematic diagram between high-pressure compressor later stages typical grade.
Fig. 2 is the blending regional change comparison diagram increased before and after axial velocity.
Fig. 3 is the comparison of boundary-layer and velocity profile variation before and after the rotor listrium using one or more embodiments
Figure.
Fig. 4 is the partial view of axial flow compressor rotor.
Fig. 5 is the signal according to the axial flow compressor rotor root listrium of a multiple embodiments from airflow direction
Figure.
Fig. 6 is according to axial flow compressor rotor root listrium showing from inverted draft direction of a multiple embodiments
It is intended to.
Specific embodiment
It is following to disclose the embodiment or embodiment of subject technology scheme described in a variety of different implementations.For simplification
The specific example of each element and arrangement is described below in disclosure, and certainly, these are only example, is not to this
The protection scope of invention is limited.Such as the fisrt feature then recorded in the description above second feature or above
It is formed, may include the embodiment that the first and second features are formed by way of directly contacting, also be included in the first He
The embodiment that supplementary features are formed between second feature, to can not directly be contacted between the first and second features.In addition,
In these disclosures may in different examples repeat reference numerals and/or letter.The repetition is in order to brief and clear
Chu itself does not indicate each embodiment being discussed and/or interstructural relationship.Further, when first element be with
The mode that second element is connected or combines describes, which includes the reality that the first and second elements are connected directly or are bonded to each other
Mode is applied, also includes so that the first and second interelements ground connection is connected or is tied each other using one or more other intervening elements additions
It closes.
Traditional seal structure as shown in Figure 1 and interstage structure form, wherein labyrinth gas seals structure obturages effect,
In the case where determining pressure difference and comb odontoid, influenced by the tip clearance and comb number of teeth mesh of comb tooth 2.The quantity of comb tooth 2 is by axis
Limitation to size.And the tip clearance of the comb tooth 2 then operating condition variation and rotation between rotary part 3 and stationary parts 1
The disturbance of rotation member shaft bias is related, it is difficult to control to ideal small gap.Change so labyrinth gas seals are difficult to make in structure
Effect is obturaged into enhancing.The axial distance of Inter-stage gap often operating conditions different from rotary part axial force variation have
It closes, also has reached the value of minimum license under normal circumstances.From the aspect of pneumatic, the size in region is blended by rotor hub air-flow
The conjunction speed of axial velocity and leakage stream speed codetermines, according to Fig.2, the leakage stream speed v between grade1Constant situation
Under, increase rotor hub axial velocity v2Blending area size can be effectively reduced, so that leakage is blended with boundary-layer between reducing grade
Loss.The technical problem to be solved is that the axial velocities for the fluid for how improving rotor hub for aftermentioned embodiment, and then subtract
Aerodynamic loss caused by being leaked between small grade.
In aftermentioned embodiment, sets about from the axial velocity for improving rotor hub fluid, propose a kind of rotor hub
Listrium circumferentially opens up the scheme of equally distributed groove, and due to the high speed rotation of rotor drum, the groove opened up can make attached face
Layer fluid generates stronger vortex, reinforces the momentum-exchange of wheel hub end wall and main flow area, so that close to fluid at wheel hub end wall
Flowing velocity is radially distributed fuller.As shown in figure 3, rotor hub boundary layer thickness is by δ by sufficient momentum-exchange
1 variation δ 2, the axial velocity that leakage stream blends between grade significantly increase.
This scheme, to increase rotor hub fluid axial velocity, is being turned in the case where cavity seal structure is constant
Sub- listrium week sets up the groove being distributed from rotor pressure face to suction surface indention, and depth of groove is along axial direction with secondary song
Line form gradually changes, and reaches maximum in the outlet of rotor hub listrium.
It is alternately arranged in the axial flow compressor of composition to a series of stator-rotors, rotor is fixed on drum barrel axis, quiet
Son is fixed on casing.To rotor blade, root is connected by rotor listrium with drum barrel axis.Embodiment as shown in Figure 4
In, the listrium of rotor blade suction surface side and its front and back extended segment are defined as a-quadrant, by the listrium of rotor blade pressure surface side
And front and back extended segment is defined as B area.The a-quadrant of two rows of adjacent rotor blades and B area are connected to become the region C, are described below
To be shown on the region C.
As shown in Figure 5 and Figure 6, the circumferentially arranged uniform gap of rotor blade root listrium, depth of groove edge flow direction is gradually
Increase, reaches maximum in rotor listrium exit.
Groove starting point is located on the straight line that rotor leading edge point is linked to be, and depth of groove is 0 at start position, such as D point in Fig. 5
And at D ' lines.
Groove terminal is located at rotor listrium exit, and groove terminal depth capacity meets: 1. depth of groove is not to be exceeded 1/2
Listrium thickness；2. depth of groove is as suitable with boundary layer thickness as possible in the case where meeting condition 1..
Groove is circumferentially uniformly distributed with zigzag, point (the E point and H in such as Fig. 6 that wherein listrium intersects with root of blade
Point), it is in zigzag highest point position, all zigzag wave peak positions (F point in such as Fig. 6) and original inner flow passage are in same
On one type face, zigzag wave trough position (G point in such as Fig. 6) is in groove lowermost end.
Number of recesses need to meet pneumatic and structural requirement simultaneously, it is pneumatic on need to reach enough mixing intensities, wanted in structure
Reduction difficulty of processing as far as possible is sought, therefore in one or more embodiments, number of recesses is 8~12.
Edge flows to fovea superior groove depth from start position position gradual change in the form of conic section to terminal, and changes in front half section
It is relatively slow, it is very fast in second half section variation.The expression of conic section is sat by starting point coordinate and listrium outlet groove deepest point
Mark codetermines.
Although the utility model is disclosed as above with preferred embodiment, its be not for limiting the utility model, it is any
Those skilled in the art without departing from the spirit and scope of the utility model, can make possible variation and modification.Cause
This, all contents without departing from technical solutions of the utility model, according to the technical essence of the utility model to above embodiments institute
Any modification, equivalent variations and the modification made, each fall within the protection scope that the utility model claims are defined.
Claims (10)
1. axial flow compressor rotor root zigzag listrium, including the rotor listrium between adjacent rotor blades, feature exists
In from a rotor blade pressure face of the adjacent rotor blades to another rotor blade on the rotor listrium is circumferential
Between suction surface setting indention be distributed multiple grooves, the multiple depth of groove along axial direction in the form of conic section by
Gradual change, and reach maximum in the outlet side of the rotor listrium.
2. axial flow compressor rotor root zigzag listrium as described in claim 1, which is characterized in that the starting point of the groove
On the straight line that rotor blade leading edge point is linked to be, depth of groove is 0 at start position.
3. axial flow compressor rotor root zigzag listrium as described in claim 1, which is characterized in that the depth of groove is not
More than 1/2 listrium thickness, and depth of groove and the interstage flow boundary layer thickness of stream of taking offence are suitable.
4. axial flow compressor rotor root zigzag listrium as described in claim 1, which is characterized in that rotor listrium and rotor
The point of root of blade intersection, is in zigzag highest point position, all zigzag wave peak positions are in same inner flow passage type
On face, zigzag wave trough position is in groove lowermost end.
5. axial flow compressor rotor root zigzag listrium as described in claim 1, which is characterized in that in flow direction, groove
Depth is and relatively slow in front half section variation from start position position gradual change in the form of conic section to terminal, second half section variation compared with
Fastly.
6. axial flow compressor, including a series of alternately arranged stators and rotor, rotor are fixed on drum barrel axis, stator is fixed on
On casing, the rotor blade root of rotor is connected by rotor listrium with drum barrel axis, which is characterized in that in the rotor listrium week
It is upwards in sawtooth from a rotor blade pressure face of adjacent rotor blades to the setting the suction surface of another rotor blade
Multiple grooves of shape distribution, the multiple depth of groove are gradually changed in the form of conic section along axial direction, and in the rotor edge
The outlet side of plate reaches maximum.
7. axial flow compressor as claimed in claim 6, which is characterized in that the starting point of the groove is located at rotor blade leading edge point
On the straight line being linked to be, depth of groove is 0 at start position.
8. axial flow compressor as claimed in claim 6, which is characterized in that the depth of groove is no more than 1/2 listrium thickness, and
And depth of groove and the interstage flow boundary layer thickness of stream of taking offence are suitable.
9. axial flow compressor as claimed in claim 6, which is characterized in that the point that rotor listrium intersects with rotor blade root,
It is in zigzag highest point position, all zigzag wave peak positions are on same inner flow passage type face, zigzag trough position
It sets in groove lowermost end.
10. axial flow compressor as claimed in claim 6, which is characterized in that in flow direction, depth of groove is from start position to end
Point position gradual change in the form of conic section, and it is relatively slow in front half section variation, it is very fast in second half section variation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820619654.6U CN208546354U (en) | 2018-04-27 | 2018-04-27 | Axial flow compressor and its rotor hub zigzag listrium |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820619654.6U CN208546354U (en) | 2018-04-27 | 2018-04-27 | Axial flow compressor and its rotor hub zigzag listrium |
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| Publication Number | Publication Date |
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| CN208546354U true CN208546354U (en) | 2019-02-26 |
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| CN201820619654.6U Active CN208546354U (en) | 2018-04-27 | 2018-04-27 | Axial flow compressor and its rotor hub zigzag listrium |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111946666A (en) * | 2020-07-20 | 2020-11-17 | 中国科学院工程热物理研究所 | Axial compressor end wall boundary layer flow regulation and control structure |
| WO2022105823A1 (en) * | 2020-11-18 | 2022-05-27 | 中国航发上海商用航空发动机制造有限责任公司 | Blade edge plates, blade ring, impeller disk, and gas turbine engine |
-
2018
- 2018-04-27 CN CN201820619654.6U patent/CN208546354U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111946666A (en) * | 2020-07-20 | 2020-11-17 | 中国科学院工程热物理研究所 | Axial compressor end wall boundary layer flow regulation and control structure |
| CN111946666B (en) * | 2020-07-20 | 2022-04-19 | 中国科学院工程热物理研究所 | Axial compressor end wall boundary layer flow regulation and control structure |
| WO2022105823A1 (en) * | 2020-11-18 | 2022-05-27 | 中国航发上海商用航空发动机制造有限责任公司 | Blade edge plates, blade ring, impeller disk, and gas turbine engine |
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