CN102927052A - Processing method for radial slot cartridge receiver - Google Patents
Processing method for radial slot cartridge receiver Download PDFInfo
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- CN102927052A CN102927052A CN2012104517291A CN201210451729A CN102927052A CN 102927052 A CN102927052 A CN 102927052A CN 2012104517291 A CN2012104517291 A CN 2012104517291A CN 201210451729 A CN201210451729 A CN 201210451729A CN 102927052 A CN102927052 A CN 102927052A
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Abstract
The invention provides a processing method for a radial slot cartridge receiver, which synthetically considers structural features of a centrifugal compressor and internal flowing state. The position in a vane diffuser passenger, which is easy to have a stall phenomenon, is provided with a radial slot along the side of a wheel cover. The processing method is characterized by processing a coverage range of a slot along the radial direction and the slot depth by using the designed result of another processing method for a circumferential slot cartridge receiver, i.e., comprising the following steps of: designing a processing proposal for the circumferential slot cartridge receiver to determine the best slot depth and the coverage range of the processed slot along the radial direction; and designing the processing proposal for the radial slot cartridge receiver, wherein the radial slot is specifically a straight slot distributed along the radial direction in a discrete manner. The basic thinking for the design is that the trend and distance of the radial slot are expected to guide the trend of low-speed fluid at the side of the diffuser wheel cover, and a reflow passage for low-speed fluid is provided, therefore, the blockage of a top passage is weakened, a stable working range of the compressor is greatly improved, and simultaneously, the peak-value efficiency and small-flow lateral pressure ratio are improved.
Description
Technical field
The present invention relates to a kind of centrifugal compressor casing processing method, particularly a kind of radial groove casing processing method.
Background technique
Centrifugal compressor has that volume is little, the single-stage pressure ratio is high and advantages of simple structure and simple, more and more is applied to many fields.In recent years, be accompanied by people for the continuous lifting of demand and the interest of microminiature energy conversion system, high rotating speed, high pressure ratio, high efficiency, wide operating mode, miniaturization have become one of important trend of centrifugal compressor development, and its performance has been proposed day by day harsh requirement.The development trend of the current high rotating speed of gas compressor, high load is to the stable operation of gas compressor and expand steady technology and proposed new challenge, is the key factor that jeopardizes gas compressor stable operation take rotating stall, surge as the UNSTEADY FLOW unstable phenomenon of representative particularly.In the actual moving process of gas compressor, after flow reached minimum stream value on the performance curve, if continue to reduce flow, unexpected variation occured in gas compressor internal flow meeting, and stall group appears in runner inside, flows into instability status, and rotating stall occurs.Further to the development of the degree of depth, surge can occur to rotating stall in compression system, causes occurring in the compression system zone of minus flow.
The generation of rotating stall can make impeller blade bear long vibration stress, cause the reduction of leaf longevity, and surge is when occuring, impeller blade and casing all will bear very large momentary force effect, can cause larger destruction, therefore, safely and steadily run in order to ensure gas compressor, must avoid these two kinds of flow unstable phenomenons of rotating stall and surge as far as possible.At present, general way is to allow gas compressor work under the state away from stalling point, namely will consider certain stall margin in the design phase.But the efficient and high parameter operation area of typical gas compressor is closed on the flow unstable border of gas compressor usually, and the way of reserving certain stall margin is a kind of great waste to the performance of gas compressor.Therefore, for the gas compressor in the practical application, wish that usually its stable operation range is wide as far as possible, so that gas compressor is approaching efficient and the work of high parameter operation area as far as possible.And widen the stable operation range of gas compressor, and postpone the generation of air-flow stall, be of great significance for the Performance And Reliability tool that improves gas compressor, also become one of key issue that the gas compressor design specialists endeavour to solve.
As a kind of Passive Control strategy of gas compressor internal flow unstability, adopt casing to process (Casing Treatments) and will help to weaken the top clearance leakage flow to the negative effect of gas compressor, improve the stall margin of gas compressor.A kind of casing processing form of extensive use is that various slot type casings are processed structure, and traditional slot type casing is processed structure and often carried out for compressor rotor, but in the same decline that often can cause efficient that enlarges gas compressor stable operation nargin.
Summary of the invention
The object of the invention is to overcome the shortcoming of above-mentioned prior art, provide a kind of and can when increasing substantially the gas compressor stable operation range, guarantee that peak efficiencies and small flow side pressure are than the radial groove casing processing method of the centrifugal compressor that also increases.
For achieving the above object, the technical solution used in the present invention is:
1) at first, do not have slotted gas compressor to carry out modeling to the wheel cap side, and its interior flow field is carried out numerical simulation and flow analysis, determine to account in the gas compressor leading flow field structure and flow performance thereof, be easy to occur the zone of stall in the clear and definite compressor passage;
2) secondly, the zone that is easy to occur stall in the compressor passage of determining according to step 1) is offered single peripheral groove and it is carried out modeling and numerical simulation along the different meridians of gas compressor wheel cap side position, relatively the steady effect of expansion of diverse location peripheral groove casing and on the impact of compressor efficiency is determined best slotting position;
3) then, the optimum position of offering peripheral groove according to gas compressor wheel cap side is the peripheral groove groove depth fixedly, changes the peripheral groove groove width, and the peripheral groove of different in width is carried out modeling and numerical simulation, compare groove width expands steady effect and compressor efficiency on the peripheral groove casing impact, thereby determine best groove width;
4) further, offer the optimum position of peripheral groove and the best groove width that step 3) obtains according to gas compressor wheel cap side, fixing peripheral groove groove width, change the peripheral groove groove depth, peripheral groove to different depth carries out modeling and numerical simulation, compare groove depth expands steady effect and compressor efficiency on the peripheral groove casing impact, thereby determine best groove depth;
5) last, according to step 2), 3), 4) the peripheral groove position of determining, groove depth and the groove width of peripheral groove, extended laterally by the peripheral groove position and to offer identical peripheral groove, determine that the groove facewidth is the spacing of adjacent slot, change the peripheral groove number, peripheral groove casing to the different slots number carries out modeling and numerical simulation, and relatively the peripheral groove number is processed the impact of expanding steady effect and compressor efficiency on casing, determines best peripheral groove number;
6) after the peripheral groove number was determined, radial process groove coverage area radially was namely from the forward position of first peripheral groove to the rear edge of last one peripheral groove;
7) forward position of radial groove overlaps with the forward position of first peripheral groove, the rear edge of radial groove overlaps with the rear edge of last peripheral groove, and the degree of depth of radial groove is chosen the best groove depth of above-mentioned peripheral groove, and radial groove has 17 groups, 17 blades of corresponding vane diffuser, every group comprises 3 radial grooves.
Described best slotting position, best groove depth, best groove width and best peripheral groove number are determined by following index:
Comprehensive stall margin improvement amount (Δ SM):
Design point/peak point efficiency change (Δ η
Des/peak):
In the formula: Q
mAnd ε
TotBe respectively mass flow rate and overall pressure tatio, subscript stall, des and peak represent respectively stalling point, design point and peak efficiencies point, parameter with subscript solid is real wall casing gas compressor parameter, the parameter of subscripting is not processor box gas compressor parameter, utilizes the steady effect of expansion that These parameters also can quantitative analysis radial groove casing processing method.
Position, described radial groove forward position width is 4.47mm, and the adjacent slot spacing is 4.47mm in the group, and the spacing of two adjacent groups groove is 8.95mm.
In the radial groove casing processing method provided by the invention, the trend of radial groove and spacing can guide the trend of Diffuser wheel cap side low velocity fluid, and for low velocity fluid provides a return flow line, help to weaken the obstruction of top passageway, increased substantially the stable operation range of gas compressor, peak efficiencies and small flow side pressure are than also increasing simultaneously.
This casing processing method can realize processing easily, and can obtain larger stall margin improvement under the prerequisite of not losing compressor efficiency, therefore has certain meaning for improving Capability of Compressor, has very high social benefit and promotional value.
Description of drawings
Fig. 1 is radial process groove schematic diagram.
Fig. 2 be have or not casing process the small size centrifugal compressor 85% design speed (30, the flow in the time of 000rpm)-efficiency characteristic curve.
Fig. 3 be have or not casing process the small size centrifugal compressor 85% design speed (30, the flow in the time of 000rpm)-pressure ratio characteristic curve.
Embodiment
Below in conjunction with accompanying drawing the present invention is described in further detail.
1) at first, do not have slotted gas compressor to carry out modeling to the wheel cap side, and its interior flow field is carried out numerical simulation and flow analysis, determine to account in the gas compressor leading flow field structure and flow performance thereof, be easy to occur the zone of stall in the clear and definite compressor passage;
2) secondly, the zone that is easy to occur stall in the compressor passage of determining according to step 1) is offered single peripheral groove and it is carried out modeling and numerical simulation along the different meridians of gas compressor wheel cap side position, relatively the steady effect of expansion of diverse location peripheral groove casing and on the impact of compressor efficiency is determined best slotting position;
3) then, the optimum position of offering peripheral groove according to gas compressor wheel cap side is the peripheral groove groove depth fixedly, changes the peripheral groove groove width, and the peripheral groove of different in width is carried out modeling and numerical simulation, compare groove width expands steady effect and compressor efficiency on the peripheral groove casing impact, thereby determine best groove width;
4) further, offer the optimum position of peripheral groove and the best groove width that step 3) obtains according to gas compressor wheel cap side, fixing peripheral groove groove width, change the peripheral groove groove depth, peripheral groove to different depth carries out modeling and numerical simulation, compare groove depth expands steady effect and compressor efficiency on the peripheral groove casing impact, thereby determine best groove depth;
5) last, according to step 2), 3), 4) the peripheral groove position of determining, groove depth and the groove width of peripheral groove, extended laterally by the peripheral groove position and to offer identical peripheral groove, determine that the groove facewidth is the spacing of adjacent slot, change the peripheral groove number, peripheral groove casing to the different slots number carries out modeling and numerical simulation, compares the peripheral groove number expands steady effect and compressor efficiency on casing impact, determines best peripheral groove number.After the peripheral groove number was determined, treatment trough coverage area radially determined immediately, that is: from the forward position of first groove to the rear edge of last a groove.
6) after above-mentioned steps is finished, the design of beginning radial groove, the forward position of radial groove overlaps with the forward position of first peripheral groove, the rear edge of radial groove is rear along overlapping with last peripheral groove, the degree of depth of radial groove is chosen the best groove depth of above-mentioned peripheral groove, radial groove has 17 groups, 17 blades of corresponding vane diffuser, and every group comprises 3 radial grooves.Position, the radial groove forward position width that generates like this is 4.47mm, and the adjacent slot spacing is 4.47mm in the group, and the spacing of two adjacent groups groove is 8.95mm.
The best slotting position of the present invention, best groove depth, best groove width and best peripheral groove number are determined by following index:
Comprehensive stall margin improvement amount (Δ SM):
Design point/peak point efficiency change (Δ η
Des/peak):
In the formula: Q
mAnd ε
TotBe respectively mass flow rate and overall pressure tatio, subscript stall, des and peak represent respectively stalling point, design point and peak efficiencies point, parameter with subscript solid is real wall casing gas compressor parameter, the parameter of subscripting is not processor box gas compressor parameter, utilizes the steady effect of expansion that These parameters also can quantitative analysis radial groove casing processing method.
According to the design process of above-mentioned radial groove casing processing method certain high rotating speed small size centrifugal compressor is carried out the processor box design, and with its action effect of experimental verification.
The design parameter of this gas compressor is as shown in table 1.
Table 1 small size centrifugal compressor design parameter
The circumferential treatment trough groove depth of initial option is 2mm, and groove width is 2.5mm, and by the circumferential treatment trough in different meridians position being expanded the comparative analysis of steady effect, the final position, circumferential treatment trough forward position of determining is R=84.75mm.
Research on the circumferential treatment trough degree of depth and width impact is found: increase the degree of depth of circumferential treatment trough and the raising that width all is conducive to compressor stall nargin, but can cause negative effect to compressor efficiency, therefore, the final circumferential treatment trough degree of depth and the width of selecting is respectively 2mm and 2.5mm.
The final circumferential treatment trough number of determining is 3, and the groove facewidth is 1.5mm, and at this moment, radial process groove coverage area radially is also definite immediately, that is: the position, forward position is R=84.75mm, and rear is R=95.25mm along the position, and the degree of depth is 2mm, as shown in Figure 1.
Fig. 2 and Fig. 3 have or not casing to process compressor efficiency, pressure ratio characteristic curve when being the part rotating speed, the experiment rotating speed is 30,000rpm, as can be seen from the figure, than real wall casing gas compressor (Solid Casing), after adopting casing to process (Treated Casing), gas compressor stable operation nargin has greatly improved, and comprehensive stall margin improvement amount reaches 22.442%, simultaneously, peak efficiencies promotes 1.454%, and the small flow side pressure is than obvious lifting is also arranged.
The above only is one embodiment of the present invention, is not whole or unique mode of execution, and the exchange of any equivalence that those of ordinary skills take technical solution of the present invention by reading present disclosure is claim of the present invention and contains.
Claims (3)
1. radial groove casing processing method is characterized in that may further comprise the steps:
1) at first, do not have slotted gas compressor to carry out modeling to the wheel cap side, and its interior flow field is carried out numerical simulation and flow analysis, determine to account in the gas compressor leading flow field structure and flow performance thereof, be easy to occur the zone of stall in the clear and definite compressor passage;
2) secondly, the zone that is easy to occur stall in the compressor passage of determining according to step 1) is offered single peripheral groove and it is carried out modeling and numerical simulation along the different meridians of gas compressor wheel cap side position, relatively the steady effect of expansion of diverse location peripheral groove casing and on the impact of compressor efficiency is determined best slotting position;
3) then, the optimum position of offering peripheral groove according to gas compressor wheel cap side is the peripheral groove groove depth fixedly, changes the peripheral groove groove width, and the peripheral groove of different in width is carried out modeling and numerical simulation, compare groove width expands steady effect and compressor efficiency on the peripheral groove casing impact, thereby determine best groove width;
4) further, offer the optimum position of peripheral groove and the best groove width that step 3) obtains according to gas compressor wheel cap side, fixing peripheral groove groove width, change the peripheral groove groove depth, peripheral groove to different depth carries out modeling and numerical simulation, compare groove depth expands steady effect and compressor efficiency on the peripheral groove casing impact, thereby determine best groove depth;
5) last, according to step 2), 3), 4) the peripheral groove position of determining, groove depth and the groove width of peripheral groove, extended laterally by the peripheral groove position and to offer identical peripheral groove, determine that the groove facewidth is the spacing of adjacent slot, change the peripheral groove number, peripheral groove casing to the different slots number carries out modeling and numerical simulation, and relatively the peripheral groove number is processed the impact of expanding steady effect and compressor efficiency on casing, determines best peripheral groove number;
6) after the peripheral groove number was determined, radial process groove coverage area radially was namely from the forward position of first peripheral groove to the rear edge of last one peripheral groove;
7) forward position of radial groove overlaps with the forward position of first peripheral groove, the rear edge of radial groove overlaps with the rear edge of last peripheral groove, and the degree of depth of radial groove is chosen the best groove depth of above-mentioned peripheral groove, and radial groove has 17 groups, 17 blades of corresponding vane diffuser, every group comprises 3 radial grooves.
2. radial groove casing processing method according to claim 1 is characterized in that: described best slotting position, best groove depth, best groove width and best peripheral groove number are determined by following index:
Comprehensive stall margin improvement amount (Δ SM):
Design point/peak point efficiency change (Δ η
Des/peak):
In the formula: Q
mAnd ε
TotBe respectively mass flow rate and overall pressure tatio, subscript stall, des and peak represent respectively stalling point, design point and peak efficiencies point, parameter with subscript solid is real wall casing gas compressor parameter, the parameter of subscripting is not processor box gas compressor parameter, utilizes the yet steady effect of expansion of quantitative analysis radial groove casing processing method of These parameters.
3. radial groove casing processing method according to claim 1, it is characterized in that: position, described radial groove forward position width is 4.47mm, and the adjacent slot spacing is 4.47mm in the group, and the spacing of two adjacent groups groove is 8.95mm.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104392018A (en) * | 2014-10-16 | 2015-03-04 | 上海交通大学 | Realization method of circular-arc inclined slit machine case based on tip flow field and geometric formulation |
| CN105715587A (en) * | 2016-01-26 | 2016-06-29 | 西安热工研究院有限公司 | Gas turbine high-pressure compressor arc inclined seam casing treatment method based on velocity-direction customization |
| CN108240356A (en) * | 2018-01-08 | 2018-07-03 | 中国科学院工程热物理研究所 | A kind of Transonic Axial-flow Compressor casing circumferential slot unitized designing method |
| CN114673690A (en) * | 2022-04-22 | 2022-06-28 | 山东建筑大学 | Gap drainage blade type diffuser for centrifugal pump |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4212585A (en) * | 1978-01-20 | 1980-07-15 | Northern Research And Engineering Corporation | Centrifugal compressor |
| CN1281953A (en) * | 1999-07-15 | 2001-01-31 | 株式会社日立制作所 | Turbomachine |
| CN101092977A (en) * | 2007-07-23 | 2007-12-26 | 北京航空航天大学 | Method for designing box of processor |
| CN102094850A (en) * | 2010-12-24 | 2011-06-15 | 北京航空航天大学 | Design method of circumferential discontinuously distributed entraining grooves of engine air system |
| DE102011005025A1 (en) * | 2011-03-03 | 2012-09-06 | Siemens Aktiengesellschaft | Resonator silencer for a radial flow machine, in particular for a centrifugal compressor |
-
2012
- 2012-11-12 CN CN201210451729.1A patent/CN102927052B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4212585A (en) * | 1978-01-20 | 1980-07-15 | Northern Research And Engineering Corporation | Centrifugal compressor |
| CN1281953A (en) * | 1999-07-15 | 2001-01-31 | 株式会社日立制作所 | Turbomachine |
| CN101092977A (en) * | 2007-07-23 | 2007-12-26 | 北京航空航天大学 | Method for designing box of processor |
| CN102094850A (en) * | 2010-12-24 | 2011-06-15 | 北京航空航天大学 | Design method of circumferential discontinuously distributed entraining grooves of engine air system |
| DE102011005025A1 (en) * | 2011-03-03 | 2012-09-06 | Siemens Aktiengesellschaft | Resonator silencer for a radial flow machine, in particular for a centrifugal compressor |
Non-Patent Citations (2)
| Title |
|---|
| 吴艳辉等: "槽式处理机匣几何结构参数的正交试验", 《航空动力学报》 * |
| 马岩等: "拓展小尺寸离心压气机级失速裕度机匣处理方案的数值研究", 《工程热物理学报》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104392018A (en) * | 2014-10-16 | 2015-03-04 | 上海交通大学 | Realization method of circular-arc inclined slit machine case based on tip flow field and geometric formulation |
| CN104392018B (en) * | 2014-10-16 | 2017-05-24 | 上海交通大学 | Realization method of circular-arc inclined slit machine case based on tip flow field and geometric formulation |
| CN105715587A (en) * | 2016-01-26 | 2016-06-29 | 西安热工研究院有限公司 | Gas turbine high-pressure compressor arc inclined seam casing treatment method based on velocity-direction customization |
| CN108240356A (en) * | 2018-01-08 | 2018-07-03 | 中国科学院工程热物理研究所 | A kind of Transonic Axial-flow Compressor casing circumferential slot unitized designing method |
| CN108240356B (en) * | 2018-01-08 | 2019-06-18 | 中国科学院工程热物理研究所 | A kind of Transonic Axial-flow Compressor casing circumferential slot unitized designing method |
| CN114673690A (en) * | 2022-04-22 | 2022-06-28 | 山东建筑大学 | Gap drainage blade type diffuser for centrifugal pump |
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