CN206449022U - Processing structure is leaked between multi stage axial flow compressor level - Google Patents
Processing structure is leaked between multi stage axial flow compressor level Download PDFInfo
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- CN206449022U CN206449022U CN201621318727.5U CN201621318727U CN206449022U CN 206449022 U CN206449022 U CN 206449022U CN 201621318727 U CN201621318727 U CN 201621318727U CN 206449022 U CN206449022 U CN 206449022U
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Abstract
The purpose of this utility model leaks processing structure between being to provide a kind of multi stage axial flow compressor level.Processing structure is leaked according between multi stage axial flow compressor of the present utility model level, the downstream Inter-stage gap in the downstream including stator and the upstream Inter-stage gap of upstream side, wherein, the inlet airflow channel of the downstream Inter-stage gap and the outlet flow path of the upstream Inter-stage gap are all tilted along the main flow direction of the stator.
Description
Technical field
The utility model leaks processing structure between being related to the multi stage axial flow compressor of aero-engine level.
Background technology
When multi stage axial flow compressor is operated, due to working conditions change or other reasons, axial flow compressor can be caused to rotate
Part is rotor, and suffered axial force changes, so as to can cause axial flow compressor rotor that vibration occurs in the axial direction.Cause
This, to avoid the rotor of rotation at a high speed and adjacent stator structure from touching mill, it is necessary between rotor structure and stator structure
Retain certain axial distance, so that between foring between the axial gap i.e. level between rotor disk and stator inner flow passage structure
Gap.Under usual situation, in order to reduce leakage between level, labyrinth gas sealses structure is used between rotor drum and stator integral shroud inwall.
But, the requirement with compressor to performance, level pressure ratio becomes more and more higher, causes stator leaf to arrange the pressure difference between import/export
More and more higher, so that leakage is difficult to be obturaged completely between causing level.Leakage flow is often to approach the side of vertical main flow between level
To returning among sprue, blended with upstream to flow, so that larger loss can be caused, larger stagnation pressure is caused in root
Loss.For high-performance multistage pressure compressor later stages, this is often one of main source of flow losses.
Utility model content
The purpose of this utility model leaks processing structure between being to provide a kind of multi stage axial flow compressor level.
Processing structure is leaked according between multi stage axial flow compressor of the present utility model level, includes the downstream in the downstream of stator
Inter-stage gap and the upstream Inter-stage gap of upstream side, wherein, the inlet airflow channel of the downstream Inter-stage gap is along the stator
Main flow direction tilt.
In one embodiment, the outlet flow path of the upstream Inter-stage gap is tilted along the main flow direction of the stator.
In one embodiment, coming from the shaft section projection of shape that processing structure is leaked between multi stage axial flow compressor level
See, at the inlet airflow channel of the downstream Inter-stage gap, the stator downstream side is along the oblique of main flow direction inclined downstream
Side, the inner flow passage molded line of the hypotenuse and the stator is into angle；Upstream edge with stator downstream adjacent rotor is upward
The continuous and derivable curve of protrusion is swum, the curve is smoothly upstream protruded vertically by close.
In one embodiment, the angle is between 30~45 degree.
In one embodiment, the upstream edge of the downstream adjacent rotor and the tangent line of the inner flow passage joint of the rotor
It is not more than 7 degree with the angle of the runner in the rotor.
In one embodiment, coming from the shaft section projection of shape that processing structure is leaked between multi stage axial flow compressor level
See, the upstream edge of the stator is the continuous and derivable curve upstream protruded, its inner flow passage molded line tie point with the stator
Tangent line and the stator inner flow passage molded line in an angle, the downstream side of the upstream adjacent rotor of the stator is upstream
The continuous and derivable curve of indent, the curve in the inner flow passage close to the upstream adjacent rotor by close to it is vertical seamlessly transit for
Inclined downstream, the wedge angle finally downstream stretched out with the inner flow passage formation of the upstream adjacent rotor, the continuous light of indent
Sliding curve near tangent and the inner flow passage of the upstream adjacent rotor are in an angle.
In one embodiment, continuous and derivable curve near tangent and the inner flow passage of the upstream adjacent rotor of indent are formed
The angle angle between 30~45 degree.
In one embodiment, the tangent line of the continuous and derivable curve of protrusion and the inner flow passage molded line tie point of the stator
With the inner flow passage molded line of the stator into angle be not more than 7 degree.
In one embodiment, the upstream airflow passage of the upstream Inter-stage gap by stator upstream adjacent rotor wheel
Disk downstream side, the downstream elongated end lower wall surface of the inner flow passage plectane of the upstream adjacent rotor, the integral shroud component of the stator
The upstream end upper wall surface of the inner flow passage plectane of upstream edge and the stator is collectively formed, the wheel disc downstream of the upstream adjacent rotor
The upstream edge of the integral shroud component of side and the stator forms the inclined outlet flow path, it is ensured that leakage current can be between level
Enter main flow along main flow direction inclination angle, the upstream end upper wall surface of the inner flow passage plectane of the stator is continuous for what is upstream protruded
Smooth curve, is seamlessly transitted to the inner flow passage of the stator, and the angle of its tangent line and the inner flow passage of the stator is not more than 7 degree.
In one embodiment, the airflow path downstream of the downstream Inter-stage gap by stator downstream adjacent rotor wheel
The integral shroud inner flow passage plectane of disk upstream edge, the upstream end upper wall surface of the inner flow passage plectane of the downstream adjacent rotor and the stator
Downstream lower wall surface collectively form, the upstream end upper wall surface of the inner flow passage plectane of the downstream adjacent rotor is seamlessly transitted to institute
State the inner flow passage of downstream adjacent rotor, the angle of the inner flow passage of its tangent line and the downstream adjacent rotor is not more than 7 degree, it is described under
The wheel disc upstream edge of trip adjacent rotor is the continuous and derivable curve upstream protruded.
Labyrinth gas sealses structure obturages effect it is determined that in the case of pressure differential and comb odontoid, by comb tooth tip clearance and
Comb number of teeth mesh is influenceed, and comb number of teeth amount is limited by axial dimension.And tooth tip clearance of combing then with rotary part and stationary part
Operating condition change between part is relevant with the eccentric disturbance of rotary part rotating shaft, it is difficult to control to preferable small gap.So, comb
Tooth is obturaged to be difficult to make in structure to improve obturages effect to strengthen.In addition to obturaging the effect of obturaging of interstitial structure in itself, level
Between interstitial structure form also have a considerable degree of influence to leakage level, mainly axial gap size and axial gap shape
The aspect factor of shape two.The axial distance of Inter-stage gap often operating conditions different from rotary part axial force change it is relevant,
The value of minimum license is generally reached.So, improving for Inter-stage gap shape can be for improving the shadow that leaks between level
Ring.Based on this, the utility model deploys from the improvement of Inter-stage gap structure in terms of stator downstream, upstream two.Stator downstream
It is the position that leakage current enters Inter-stage gap from main flow, this part axial gap structure is changed to along main flow direction downstream to incline
Oblique structure type, compared to original vertical structure, leakage current is more difficult to enter Inter-stage gap.Stator integral shroud upstream is to let out
Gas leakage stream returns to the position of main flow from Inter-stage gap, and this is also that leakage current causes greater loss with main flow generation blending
Region, similarly, the structure of this part are similar with downstream, make the structure type along main flow direction inclined downstream into, relative to
Typical structure, will leak out air-flow along the inclined structure of main flow direction and obtains momentum component along main flow direction, and vertical main flow
Momentum component reduces, it is contemplated that can effectively reduce the blending with main flow, reduces loss.Under viscous effect, angle of inclination will make to let out
Gas leakage stream will carry out downstream along Gu Bi, without separating, it could even be possible to being conducive to the boundary layer flow in downstream improves.Therefore
The utility model has the advantages that：
1. reducing Inter-stage gap leakage current flow, weaken blending of the Inter-stage gap leakage current to main flow and act on, improve
Compressor efficiency；
2. under the premise of realizing the control leaked Inter-stage gap, it is expected to relax labyrinth gas sealses to the requirement of comb tooth tip clearance,
Reduce comb number of teeth mesh, be conducive to improving the safety in operation of compressor, simplify structure.
Brief description of the drawings
The above and other feature of the present utility model, property and advantage will be by with reference to the accompanying drawings and examples
Description and become readily apparent from, wherein：
Fig. 1 is the signal according to the first embodiment of leakage processing structure between multi stage axial flow compressor of the present utility model level
Figure.
Fig. 2 is the signal according to the second embodiment of leakage processing structure between multi stage axial flow compressor of the present utility model level
Figure.
Embodiment
With reference to specific embodiments and the drawings, the utility model is described in further detail, elaborates in the following description
More details are in order to fully understand the utility model, but the utility model obviously can be different from what this was described with a variety of
Other manner is implemented, and those skilled in the art can be in the case of without prejudice to the utility model intension according to practical application feelings
Condition makees similar popularization, deduction, therefore should not limit protection domain of the present utility model with the content of this specific embodiment.
Mainly the utility model is illustrated from structural principle for embodiment shown in Fig. 1.Implementation shown in Fig. 2
Mainly the utility model is illustrated from concrete structure for example.
Fig. 1 is the shaft section projection of shape of leakage processing structure between multi stage axial flow compressor level, wherein, stator upstream edge 1
The outlet flow path along the inclined upstream Inter-stage gap of main flow direction is constituted with the downstream side 3 of upstream adjacent rotor.On stator
Trip side 1 is the continuous and derivable curve that upstream protrudes, its tangent line and the interior stream of stator with the inner flow passage molded line tie point of stator
The angle 5 of road molded line is not more than 7 degree.Upstream adjacent rotor downstream side 3 is the continuous and derivable curve of upstream indent, and this curve exists
By being seamlessly transitted close to vertical as inclined downstream during close to upstream adjacent rotor inner flow passage, finally with being flowed in the adjacent rotor of upstream
The angle of wedge angle, herein the continuous and derivable curve near tangent of indent and upstream adjacent rotor inner flow passage that road formation is downstream stretched out
7 size, can be small as much as possible on the premise of intensity and structural requirement is met, and suitable angle may be at 30~45 degree
Between.The upstream edge 2 of stator downstream side 4 and downstream adjacent rotor constitutes the entrance along the inclined downstream Inter-stage gap of main flow direction
Gas channel.Stator downstream side 4 is in the hypotenuse that the part of the inner flow passage close to stator is along main flow direction inclined downstream, and this is oblique
The size of the angle 8 of the inner flow passage molded line of side and stator, can be as much as possible on the premise of intensity and structural requirement is met
Small, suitable angle may be between 30~45 degree.And part of the stator downstream side 4 away from stator inner flow passage, it can only need to protect
The upstream edge 2 held with downstream adjacent rotor meets desired axial distance.The upstream edge 2 of downstream adjacent rotor is upstream
The continuous and derivable curve of protrusion, it is shaped as down pyriform, from the bottom up or from radially from inside to outside, curve is by close to vertically
Smoothly upstream protrude.The tangent line of the upstream edge 2 of downstream adjacent rotor and the inner flow passage joint of the downstream adjacent rotor is with turning
The angle 6 of sub- inner flow passage is not more than 7 degree.
In Fig. 1, correspondence upstream Inter-stage gap, the stator downstream side 4 of downstream Inter-stage gap, the tool of upstream edge 1 is not shown
Shape or composition, while the downstream side 3 of upstream adjacent rotor is also not shown, the shape of the upstream edge 2 of downstream adjacent rotor
Or constitute.Next, the composition that these sides are understood in embodiment can be shown with Fig. 2, it can be mentioned that these sides
Composition may have change or modification.Usual high-pressure compressor later stages are using annular tongue-and-groove attachment structure, so above and below rotor
The shape on trip side is realized jointly by rotor disk with rotor blade listrium.It is entirely axisymmetric due to leaking processing structure between level
Structure, therefore embodiment illustrated in fig. 2 can illustrate clear completely by shaft section perspective view.
Fig. 2 is illustrated by taking the quiet rotor of high-pressure compressor multistage axial flow as an example.Relative to conventional quiet rotor, aftermentioned reality
On the one hand apply example is the interstitial structure carry out type face repairing type constituted to stator integral shroud and downstream rotor wheel disc, and axial gap is constituted
Gas channel enter line tilt along main flow direction, suitable inclination angle and gas channel shape are realized, to effectively reduce between entrance
The leakage current amount of gap；On the other hand the interstitial structure carry out type face repairing type constituted to stator integral shroud and upstream rotor wheel disc, will
The gas channel that axial gap is constituted enters line tilt along main flow direction, suitable inclination angle and gas channel shape is realized, to have
Effect weakens the blending of leakage current and main flow.
Inter-stage gap structure in view of high-pressure compressor later stages is axisymmetric structure, therefore description below completely
It will be carried out mainly for correlated parts upstream and downstream shaft section projection type face.As shown in Fig. 2 stator 9 and upstream adjacent rotor 10 with
Downstream adjacent rotor 11 constitutes the upstream and downstream part of Inter-stage gap.The gas channel of upstream Inter-stage gap is by adjacent turn of upstream
The sub- downstream side 21 of wheel disc 12, the downstream elongated end lower wall surface 20 of upstream adjacent rotor inner flow passage plectane 14, stator integral shroud component 16
Upstream edge 18 and the upstream end upper wall surface 19 of stator inner flow passage plectane 17 collectively form.The downstream side 21 of upstream adjacent rotor wheel disc 12
And the upstream edge 18 of stator integral shroud component 16 ensures that leakage current between level appropriate can be entered with sufficiently small along main flow direction inclination angle
Enter main flow, the upstream end upper wall surface 19 of stator inner flow passage plectane 17 is seamlessly transitted to stator blade inner flow passage, its tangent line and inner flow passage
Angle be not more than 7 degree, to prevent leakage current from air-flow separation occurring here.The gas channel of downstream Inter-stage gap is by downstream
The upstream edge 22 of adjacent rotor wheel disc 13, the upstream end upper wall surface 23 of downstream adjacent rotor inner flow passage plectane 15 and stator integral shroud inner flow passage
The downstream lower wall surface 24 of plectane 17 is collectively formed, and forms one along the inclined passage of main flow direction, to reduce between level
The leakage current of gap.The upstream end upper wall surface 23 of downstream adjacent rotor inner flow passage plectane 15 is seamlessly transitted to downstream adjacent rotor 11
Runner, and the angle of its tangent line and inner flow passage is not more than 7 degree, to reduce the possibility for producing air-flow separation.In addition, adjacent turn of downstream
" pyriform " curve form of the sub- upstream edge 22 of wheel disc 13, under compressor operating condition, can induce wall boundary layer airflow and exists
Migrated upwards along wall toward main flow under centrifugal action, and enter Inter-stage gap using its kinetic energy to resist leakage current.
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 are not being departed from spirit and scope of the present utility model, can make possible variation and modification.Cause
This, every content without departing from technical solutions of the utility model, according to technical spirit of the present utility model to above example institute
Any modification, equivalent variations and the modification made, each fall within the protection domain that the utility model claim is defined.
Claims (10)
1. leak processing structure between multi stage axial flow compressor level, including stator downstream downstream Inter-stage gap and upstream side
Upstream Inter-stage gap, it is characterised in that the inlet airflow channel of the downstream Inter-stage gap inclines along the main flow direction of the stator
Tiltedly.
2. leak processing structure between multi stage axial flow compressor level as claimed in claim 1, it is characterised in that between the upstream stage
The outlet flow path in gap is tilted along the main flow direction of the stator.
3. leak processing structure between multi stage axial flow compressor level as claimed in claim 1, it is characterised in that from the multistage axial flow
Between compressor stage leak processing structure shaft section projection of shape from the point of view of, the inlet airflow channel of the downstream Inter-stage gap
Place, the stator downstream side is the hypotenuse along main flow direction inclined downstream, the inner flow passage molded line of the hypotenuse and the stator
Into angle；Upstream edge with stator downstream adjacent rotor is the continuous and derivable curve upstream protruded, and the curve is by approaching
Smoothly upstream protrude vertically.
4. leak processing structure between multi stage axial flow compressor level as claimed in claim 3, it is characterised in that the angle is 30
Between~45 degree.
5. leak processing structure between multi stage axial flow compressor level as claimed in claim 3, it is characterised in that the downstream is adjacent
The upstream edge of rotor and the angle of the tangent line and the runner in the rotor of the inner flow passage joint of the rotor are not more than 7 degree.
6. leak processing structure between multi stage axial flow compressor level as claimed in claim 2, it is characterised in that from the multistage axial flow
Leaked between compressor stage processing structure shaft section projection of shape from the point of view of, the upstream edge of the stator is the company upstream protruded
Continuous smooth curve, the tangent line of inner flow passage molded line tie point of itself and the stator and the inner flow passage molded line of the stator are into a folder
Angle, the downstream side of the upstream adjacent rotor of the stator is the continuous and derivable curve of upstream indent, and the curve is close to described
By being seamlessly transitted close to vertical as inclined downstream during the inner flow passage of upstream adjacent rotor, finally with the upstream adjacent rotor
The wedge angle that inner flow passage formation is downstream stretched out, the continuous and derivable curve near tangent of indent and the interior stream of the upstream adjacent rotor
Road is in an angle.
7. leak processing structure between multi stage axial flow compressor level as claimed in claim 6, it is characterised in that this of indent is continuous
The angle of the tangent line of smooth curve and the angle of the inner flow passage of upstream adjacent rotor formation is between 30~45 degree.
8. leak processing structure between multi stage axial flow compressor level as claimed in claim 6, it is characterised in that the company of protrusion
The tangent line of inner flow passage molded line tie point of continuous smooth curve and the stator and the inner flow passage molded line of the stator into angle not
More than 7 degree.
9. leak processing structure between multi stage axial flow compressor level as claimed in claim 2, it is characterised in that between the upstream stage
The upstream airflow passage in gap is by the wheel disc downstream side of stator upstream adjacent rotor, the inner flow passage of the upstream adjacent rotor
The upstream of the inner flow passage plectane of the downstream elongated end lower wall surface of plectane, the upstream edge of the integral shroud component of the stator and the stator
End upper wall surface is collectively formed, and the upstream edge of the wheel disc downstream side of the upstream adjacent rotor and the integral shroud component of the stator is formed
The inclined outlet flow path, it is ensured that leakage current can enter main flow, the stator with suitable main flow direction inclination angle between level
The upstream end upper wall surface of inner flow passage plectane be the continuous and derivable curve that upstream protrudes, seamlessly transit to the interior stream of the stator
Road, the angle of its tangent line and the inner flow passage of the stator is not more than 7 degree.
10. leak processing structure between multi stage axial flow compressor level as claimed in claim 1, it is characterised in that the downstream stage
Between gap airflow path downstream by the wheel disc upstream edge of stator downstream adjacent rotor, the interior stream of the downstream adjacent rotor
The downstream lower wall surface of the upstream end upper wall surface of road plectane and the integral shroud inner flow passage plectane of the stator is collectively formed, the downstream
The upstream end upper wall surface of the inner flow passage plectane of adjacent rotor is seamlessly transitted to the inner flow passage of the downstream adjacent rotor, its tangent line with
The angle of the inner flow passage of the downstream adjacent rotor is not more than 7 degree, and the wheel disc upstream edge of the downstream adjacent rotor is upstream
The continuous and derivable curve of protrusion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621318727.5U CN206449022U (en) | 2016-12-02 | 2016-12-02 | Processing structure is leaked between multi stage axial flow compressor level |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621318727.5U CN206449022U (en) | 2016-12-02 | 2016-12-02 | Processing structure is leaked between multi stage axial flow compressor level |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110094364A (en) * | 2018-01-31 | 2019-08-06 | 中国航发商用航空发动机有限责任公司 | A kind of rotor blade and axial flow compressor |
| CN113898421A (en) * | 2021-10-10 | 2022-01-07 | 中国航发沈阳发动机研究所 | Compressor stator inner ring and rotor stator sealing connection structure thereof |
-
2016
- 2016-12-02 CN CN201621318727.5U patent/CN206449022U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110094364A (en) * | 2018-01-31 | 2019-08-06 | 中国航发商用航空发动机有限责任公司 | A kind of rotor blade and axial flow compressor |
| CN113898421A (en) * | 2021-10-10 | 2022-01-07 | 中国航发沈阳发动机研究所 | Compressor stator inner ring and rotor stator sealing connection structure thereof |
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