CN102162471A - Ellipse/circular arc chute processing machine box - Google Patents
Ellipse/circular arc chute processing machine box Download PDFInfo
- Publication number
- CN102162471A CN102162471A CN2011101130598A CN201110113059A CN102162471A CN 102162471 A CN102162471 A CN 102162471A CN 2011101130598 A CN2011101130598 A CN 2011101130598A CN 201110113059 A CN201110113059 A CN 201110113059A CN 102162471 A CN102162471 A CN 102162471A
- Authority
- CN
- China
- Prior art keywords
- ellipse
- circular arc
- design
- machine box
- processing machine
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to an ellipse/circular arc chute processing machine box applying to a rotor blade tip end region of an axial flow compressor. For the design of the ellipse or circular arc chute processing machine box, the greater flow loss of the processing chute caused by the rectangular and trapezoid design of the traditional processing machine box is taken into account. Through the reasonable design of a geometric construction type of the processing chute, namely the combination design that an ellipse shape is adopted at the R direction (radial) and a circular arc shape is adopted at the Z direction (axial), the greater low loss caused by the rectangular and trapezoid design is avoided, thus the efficiency is not reduced, meanwhile the stall margin of the compressor is improved greatly for the ellipse or circular arc chute processing machine box.
Description
Technical field
The present invention relates to a kind of device that improves the gas compressor stability margin, refer in particular to and a kind ofly can obviously improve the gas compressor stability margin and the ellipse and the arc slot casing treatment that do not reduce of its peak efficiencies simultaneously.
Background technique
Gas compressor is widely used in aeroengine and the industrial production.Along with improving constantly of compressor stage loading factor, the instability of gas compressor flows and shows day by day for outstanding, as rotating stall, surge etc., has greatly limited the further lifting of gas compressor performance.When rotating stall, exist one or more low energy stall group to rotate along gas compressor circumferential, the performance of gas compressor can descend suddenly, flow, pressure ratio and efficient all reduce as far as possible, and can produce periodic excitation force to compressor blade, even cause the generation of surge, very harmful.Therefore people have taked a lot of methods to postpone gas compressor and have rotated wild effects such as stall, to enlarge its stable operation nargin.
In order to enlarge the stability margin of gas compressor, the worker has done a lot of research work both at home and abroad.The steady effect of the expansion of processor box technology is considered to very obvious, and practicability is very strong, thereby has obtained using more widely.Fig. 1-Fig. 2 has provided two kinds of typical processor casing structure forms.
As shown in Figure 1, axial chute processor casing is axially grooved at casing upper edge gas compressor, radially the forming an angle of its groove depth direction and gas compressor.When the groove depth direction aimed at flow path direction, no matter incoming flow was equal uniform flow or the import distortion takes place, and stability margin all has bigger improvement.But the shortcoming of this class processor box is that the improvement of stability margin is a cost with the efficient of loss gas compressor.
As shown in Figure 2, tangential chute processor casing is that the groove depth direction can have different angles at the tangential fluting of casing upper edge blade tip primitive.Under the uniform incoming flow situation, the growth of stability margin is only second to axial chute processor casing, and the loss of compressor efficiency is also lacked than axial chute.
Sum up traditional processor box technology, have such shortcoming: when improving the stability margin of gas compressor always with the cost that is reduced to of adiabatic efficiency.This cost is generally about 1%-3%.On aeroengine, the decline of the adiabatic efficiency of gas compressor means that fuel consume can be more.
Why traditional processor box can reduce the peak efficiencies of gas compressor, one of them very important reasons be geometrical construction design unreasonable of treatment trough.The treatment trough of traditional processor box has at least one to be rectangle or trapezoidal design in R (radially), Z (axially) and three directions of θ (circumferentially), and the design of this blunt form is inevitable to cause bigger eddy loss in the angular region of treatment trough.
Therefore, how from the geometrical construction of optimization process groove, design the original intention that the less processor box of flow losses in a kind of treatment trough becomes work of the present invention.
Summary of the invention
Shortcoming at above-mentioned conventional process casing technology exists the invention provides a kind of ellipse and arc slot casing treatment, and the feature of this processor box is: treatment trough adopts the ellipse design in R direction (radially); Treatment trough adopts the circular arc type design in θ direction (circumferentially); The direction of the rear end of treatment trough and rotator tip primitive level mean camber line is roughly the same on Z direction (axially), and the front end edge of treatment trough is axial.
The design method of this ellipse and arc slot casing treatment is as follows:
(1) ellipse and arc slot casing treatment treatment trough number N are generally got 6～9 times of number of rotor blades;
(2) treatment trough axis projection length L
HDetermine
Total axis projection length L of treatment trough
H, its preliminary value changes in certain limit:
L
H＝0.7L
b～1.3L
b
L in the following formula
bAxial chord length for rotator tip primitive level blade profile.
(3) rule of thumb, treatment trough radial skew angle Alpha gets 40 ° of-60 ° of scopes
(4) treatment trough adopts ellipse in R direction (radially)
Long axis of ellipse is the distance of treatment trough front end and back end, groove depth a (length of 1/2 ellipse short shaft)=0.3～0.5L
H
(5) treatment trough adopts circular arc type in θ direction (circumferentially)
(6) overlap joint of treatment trough measures 35%
(7) the unlimited ratio of processor box is 50%
This structure all compares slick and sly on all directions, has avoided conventional process groove rectangle or trapezoidal design on certain direction, can reduce the flow losses of treatment trough, thereby in the stall margin that significantly improves gas compressor, peak efficiencies does not reduce.
Description of drawings
Fig. 1 is the axial chute processor casing schematic representation;
Fig. 2 is tangential chute processor casing schematic representation;
Fig. 3 is schematic representation (L of the invention process
bAxial chord length for rotator tip primitive level blade profile);
Fig. 4 is the view (L of the present invention in θ (circumferentially), Z (axially) and R (radially) direction
HBe treatment trough axis projection length, L
bBe the axial chord length of rotator tip primitive level blade profile, Alpha is treatment trough radial skew angle, and a is a groove depth, and A-A is the sectional view along this face, and the B view is a top view);
Fig. 5 is applied to the characteristic line of certain transonic compressor single rotor design speed numerical calculation for the present invention.
Embodiment
With certain transonic compressor single rotor is that example illustrates the specific embodiment of the present invention, and table 1 is the basic pneumatic and structural parameter of this transonic compressor single rotor.
Table 1 is the axial flow compressor rotor design parameter transonic speed
Carry out following design according to the design method in the summary of the invention:
(1) determines the number N=17 * 6=102 of treatment trough
(2) the axis projection length L of treatment trough
H=1.085 * 35mm=38mm, L
b=35mm
(3) treatment trough radial skew angle Alpha gets 45 °
(4) treatment trough is at disciform major axis of R (radially) and L
H=1.085 * 35mm=38mm, 1/2 minor axis a=14mm
(5) treatment trough adopts circular arc type at Z (axially), and the overlap joint of treatment trough measures 35%, and the unlimited ratio of processor box is 50%.
Claims (2)
1. ellipse and arc slot casing treatment, the treatment trough that it is characterized in that ellipse of the present invention and arc slot casing treatment is radially adopting ellipse and in the Combination Design that circumferentially adopts circular arc type.
2. ellipse as claimed in claim 1 and arc slot casing treatment is characterized in that treatment trough is the distance of treatment trough front end and back end in radially long axis of ellipse, and minor axis is 2 times of groove depth a, and a is 0.3～0.5L
H, L
HBe the total axis projection length of treatment trough.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101130598A CN102162471A (en) | 2011-05-03 | 2011-05-03 | Ellipse/circular arc chute processing machine box |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011101130598A CN102162471A (en) | 2011-05-03 | 2011-05-03 | Ellipse/circular arc chute processing machine box |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102162471A true CN102162471A (en) | 2011-08-24 |
Family
ID=44463866
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011101130598A Pending CN102162471A (en) | 2011-05-03 | 2011-05-03 | Ellipse/circular arc chute processing machine box |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102162471A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102606529A (en) * | 2012-03-28 | 2012-07-25 | 杭州诺沃能源科技有限公司 | Processing case structure for gas compressor of aircraft engine |
| CN102705256A (en) * | 2012-05-25 | 2012-10-03 | 北京航空航天大学 | Asymmetric double-circular-arc chute processing casing |
| CN105298923A (en) * | 2014-06-17 | 2016-02-03 | 中国科学院工程热物理研究所 | Front seam and rear groove type casing treatment stability enhancement device for gas compressor |
| CN110886724A (en) * | 2019-12-16 | 2020-03-17 | 中国科学院工程热物理研究所 | Axial seam type treatment casing |
| CN112283167A (en) * | 2020-11-20 | 2021-01-29 | 西安热工研究院有限公司 | Circumferential groove type casing treatment design method for axial flow compressor |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08159097A (en) * | 1994-12-08 | 1996-06-18 | Ishikawajima Harima Heavy Ind Co Ltd | Fan and casing of compressor |
| CN101566170A (en) * | 2009-05-21 | 2009-10-28 | 北京航空航天大学 | Non-axisymmetrical circular-arc slant slot-shaped hub excitation generator |
| CN101832302A (en) * | 2010-05-13 | 2010-09-15 | 北京航空航天大学 | Wake flow impact generator of circumferential multiple partitions |
| CN101900134A (en) * | 2010-05-13 | 2010-12-01 | 北京航空航天大学 | Novel arc slot casing treatment |
-
2011
- 2011-05-03 CN CN2011101130598A patent/CN102162471A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH08159097A (en) * | 1994-12-08 | 1996-06-18 | Ishikawajima Harima Heavy Ind Co Ltd | Fan and casing of compressor |
| CN101566170A (en) * | 2009-05-21 | 2009-10-28 | 北京航空航天大学 | Non-axisymmetrical circular-arc slant slot-shaped hub excitation generator |
| CN101832302A (en) * | 2010-05-13 | 2010-09-15 | 北京航空航天大学 | Wake flow impact generator of circumferential multiple partitions |
| CN101900134A (en) * | 2010-05-13 | 2010-12-01 | 北京航空航天大学 | Novel arc slot casing treatment |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102606529A (en) * | 2012-03-28 | 2012-07-25 | 杭州诺沃能源科技有限公司 | Processing case structure for gas compressor of aircraft engine |
| CN102705256A (en) * | 2012-05-25 | 2012-10-03 | 北京航空航天大学 | Asymmetric double-circular-arc chute processing casing |
| CN105298923A (en) * | 2014-06-17 | 2016-02-03 | 中国科学院工程热物理研究所 | Front seam and rear groove type casing treatment stability enhancement device for gas compressor |
| CN105298923B (en) * | 2014-06-17 | 2018-01-02 | 中国科学院工程热物理研究所 | Slot type treated casing expands stabilization device after being stitched before compressor |
| CN110886724A (en) * | 2019-12-16 | 2020-03-17 | 中国科学院工程热物理研究所 | Axial seam type treatment casing |
| CN110886724B (en) * | 2019-12-16 | 2021-10-01 | 中国科学院工程热物理研究所 | Axial seam type treatment casing |
| CN112283167A (en) * | 2020-11-20 | 2021-01-29 | 西安热工研究院有限公司 | Circumferential groove type casing treatment design method for axial flow compressor |
| CN112283167B (en) * | 2020-11-20 | 2022-04-01 | 西安热工研究院有限公司 | Circumferential groove type casing treatment design method for axial flow compressor |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102162471A (en) | Ellipse/circular arc chute processing machine box | |
| CN101915126B (en) | Tandem blade type mixed-flow or radial-flow turbine | |
| KR20140012155A (en) | Nozzle blade | |
| CN102162472A (en) | Multi-arc chute processing machine box | |
| CN101900134A (en) | Novel arc slot casing treatment | |
| CN103256248B (en) | Impeller and comprise the centrifugal compressor of this impeller | |
| CN104196573A (en) | Low-pressure last stage blade of rotating speed-variable air cooling industrial steam turbine with steam exhaust area of 3.6 m2 | |
| CN102108881B (en) | Secondary final stage blade for half-RPM (Revolution per Minute) nuclear turbine | |
| CN100482950C (en) | Non-axisymmetric blade tip actuation generator | |
| CN105604611A (en) | Variable-geometry turbine with strake wing structure of moving blade | |
| CN204099272U (en) | A kind of low specific-speed centrifugal pump impeller | |
| CN101737359B (en) | Asymmetric self-circulation processing case with slotting position of sine distribution for centrifugal compressor | |
| CN204164031U (en) | A kind of impeller of centrifugal air compressor | |
| CN203272243U (en) | Treated casing for gas aeroengines | |
| CN101418821A (en) | Non-axisymmetric combination processor box opening with honeycomb hole and axial tapered slot simultaneously | |
| CN102705256A (en) | Asymmetric double-circular-arc chute processing casing | |
| CN201190695Y (en) | Nonsymmetrical combination casing treatment | |
| CN100457548C (en) | Non-axial-symmetry combination processing machine box | |
| CN210343845U (en) | Semi-open type centrifugal impeller with splitter blades | |
| CN101566171A (en) | Axial inclined slot and reverse vortex shallow slot circumferential non-axisymmetrical combination type processor box | |
| US20180258945A1 (en) | Turbocharger compressor impeller with serrated leading edges | |
| CN108506249B (en) | Groove end wall processing method for axial flow compressor | |
| CN201152282Y (en) | Non- axial symmetry blade tip excitation generator | |
| CN213628157U (en) | Circumferential groove type casing processing structure for axial flow compressor | |
| CN106968986A (en) | Seam processor box and compressor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20110824 |