CN101545818A - Turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure - Google Patents
Turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure Download PDFInfo
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- CN101545818A CN101545818A CN200910143114A CN200910143114A CN101545818A CN 101545818 A CN101545818 A CN 101545818A CN 200910143114 A CN200910143114 A CN 200910143114A CN 200910143114 A CN200910143114 A CN 200910143114A CN 101545818 A CN101545818 A CN 101545818A
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Abstract
The invention belongs to turbo-charger technical field, particularly relating to centrifugal compressor interstage pressure test structure, especially a turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure. The test structure includes a compressor spiral casing, a blower impeller and a compressor back disk. The spiral casing is fixed on the compressor back disk through bolts. The blower impeller is fixed on the shaft seal sleeve of the compressor back disk by the shaft end nuts. The compressor spiral casing is divided into a split spiral casing and a sleeve at the position of diameter 180 mm in the middle on the side wall of the compressor spiral casing diffuser. The split spiral casing and the sleeve are fixably connected with the contact surface of the sleeve by the hot charging face of the split spiral casing. The invention measures the inner pressure of the spiral casing and the diffuser on the centrifugal compressor prototype model machine and measures the enclosing cover pressure in the circumferential direction 360 DEG scope. The test structure has simple structure and easy implement based on the prototype model machine.
Description
Technical field
The invention belongs to turbo-charger technical field, be specifically related to a kind of centrifugal compressor interstage pressure test structure, especially turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure.
Background technology
Along with the raising of power density, high pressure ratio and UHV (ultra-high voltage) become current development trend than turbosupercharger.Yet be accompanied by the raising of pressure ratio, centrifugal compressor enters the mobile state of transonic speed, and its flow range sharply narrows down and decrease in efficiency; While transonic speed centrifugal compressor structure is complicacy very, and the existing CFD numerical simulation technology of simple dependence has been difficult to obtain reliable result.For expanding transonic speed state flow weight range and raising the efficiency, carry out researchs such as flow control method and transonic flow field, pressure field test and become current development trend and research focus.
With regard to means of testing, interior flow field is measured laser velocimeter means such as PIV of employing or LDV more, for the interior flow field test of the transonic speed centrifugal compressor of high rotating speed small scale high turbulence, difficulty of test and testing cost are very big, and test specification is very high.Even technology such as the employing model amplifies, model is abstract also are difficult to obtain the flow field information that the needed end wall of deviser, boundary-layer etc. are located.For this reason, just need to adopt the method for gaging pressure field to obtain flow field information, with support study dies flow control method and raising pneumatic plant performance.
Domestic to centrifugal compressor interstage pressure Research of measuring rareness, once discovered and seized the research information of relevant spiral case static pressure test, do not obtain the research information of enclosing cover for impeller pressure test.
The scholar was once arranged to enclosing cover for impeller and the diffuser test pressure of layouting in detail abroad, and acquisition flow field information, according to discovering and seizing information, all on major diameter impeller more than the diameter 200mm or exaggeration model, obtain, many models that also carried out are abstract, such as the lengthening diffuser, replace spiral case etc. with gas collector; Do not have to find relevant at the report that carries out static pressure measurement between compressor stage on the prototype.
Summary of the invention
The objective of the invention is test result, and propose a kind of turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure for acquisition turbosupercharger single-stage prototype centrifugal pneumatic plant interstage pressure.
The technical solution adopted in the present invention is: a kind of turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure, comprise compressor volute, compressor impeller, pneumatic plant back of the body dish, spiral case by bolt on pneumatic plant back of the body dish, compressor impeller is fixed on the pneumatic plant back of the body dish axle big envelope by shaft end nut, in diameter 180mm position, compressor volute diffuser sidewall middle part compressor volute is divided into split spiral case and sleeve two parts, split spiral case and sleeve are fixedly connected by the hot charging face of split spiral case and the surface of contact of sleeve, at each uniform 8 enclosing cover for impeller pressure gaging hole of sleeve deviated splitter vane import blade tip correspondence position, import and export each uniform 8 diffuser pressure gaging hole of position at pneumatic plant back of the body dish diffuser sidewall, along circumferential 90 °～360 ° uniform 7 the volute pressure gaging holes of split spiral case die joint, arrange 2 volute pressure gaging holes at aditus laryngis and spiral case outlet simultaneously, arrange 1 volute pressure gaging hole in 30 °～90 ° scopes, whole level amounts to 42 pressure gaging holes.
The diameter of described enclosing cover for impeller pressure gaging hole, diffuser pressure gaging hole and volute pressure gaging hole is 0.5～1.0mm.
Beneficial effect of the present invention: the present invention can measure on the centrifugal compressor prototype machine in spiral case and the diffuser internal pressure, at circumferential 360 ° of scope build-in test enclosing cover for impeller place pressure.Test structure is based on prototype machine, and is simple in structure, realizes easily.
Description of drawings
The present invention has 3 width of cloth accompanying drawings, and wherein Fig. 1 is a most preferred embodiment of the present invention, also can make the accompanying drawing of specification digest.
Fig. 1, be the general structure synoptic diagram of turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure;
Fig. 2 a, be the split spiral case blank stereographic map of turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure;
Fig. 2 b, be the spiral case sleeve blank stereographic map of turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure;
Fig. 2 c, be the split spiral case and the spiral case sleeve processed finished products stereographic map of turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure;
Fig. 3 a, be that the enclosing cover for impeller of turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure and volute pressure gaging hole connect stereographic map;
Fig. 3 b, be that the diffuser inlet and outlet pressure gaging hole of turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure connects the back stereographic map;
Fig. 3 c, be that the diffuser inlet and outlet pressure gaging hole of turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure connects front perspective view.
Embodiment:
Below in conjunction with accompanying drawing most preferred embodiment of the present invention is further described.
As Fig. 1, Fig. 2 a, Fig. 2 b, Fig. 2 c, Fig. 3 a, Fig. 3 b, shown in Fig. 3 c, a kind of turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure, comprise compressor volute, compressor impeller 6, pneumatic plant back of the body dish 7, spiral case by bolt on pneumatic plant back of the body dish 7, compressor impeller 6 is fixed on 7 big envelopes of pneumatic plant back of the body dish by shaft end nut, in diameter 180mm position, compressor volute diffuser sidewall middle part compressor volute is divided into split spiral case 1 and sleeve 2 two parts, split spiral case 1 and sleeve 2 are fixedly connected by the hot charging face 3 of split spiral case 1 and the surface of contact 4 of sleeve 2, at each uniform 8 enclosing cover for impeller pressure gaging hole 5 of sleeve 2 deviated splitter vane import blade tip correspondence positions, coil 7 diffuser sidewalls at the pneumatic plant back of the body and import and export each uniform 8 diffuser pressure gaging hole 9 of position, along circumferential 90 °～360 ° uniform 7 the volute pressure gaging holes 8 of split spiral case 1 die joint, arrange 2 volute pressure gaging holes at aditus laryngis and spiral case outlet simultaneously, arrange 1 volute pressure gaging hole in 30 °～90 ° scopes, whole level amounts to 42 pressure gaging holes.
The diameter of enclosing cover for impeller pressure gaging hole 5, diffuser pressure gaging hole 9 and volute pressure gaging hole 8 is 0.5～1.0mm.
Its course of work is that the static pressure at the corresponding wheel cap wall of deviated splitter vane import blade tip place is derived through pressure tube 10 by enclosing cover for impeller pressure gaging hole 5, reaches low pressure sensor; Diffuser is imported and exported wall static pressure and is coiled 7 diffuser lateral wall pressure gaging holes 9 through pressure tube 11 derivation by the pneumatic plant back of the body, reaches high pressure sensor; Spiral case die joint internal face static pressure is derived through pressure tube 12 by volute pressure gaging hole 8, reaches high pressure sensor.
Claims (2)
1, a kind of turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure, comprise compressor volute, compressor impeller (6), pneumatic plant back of the body dish (7), spiral case by bolt on pneumatic plant back of the body dish (7), compressor impeller (6) is fixed on pneumatic plant back of the body dish (7) the axle big envelope by shaft end nut, it is characterized in that: compressor volute is divided into split spiral case (1) and sleeve (2) two parts in diameter 180mm position, compressor volute diffuser sidewall middle part, split spiral case (1) and sleeve (2) are fixedly connected by the hot charging face (3) of split spiral case (1) and the surface of contact (4) of sleeve (2), at each uniform 8 enclosing cover for impeller pressure gaging hole (5) of sleeve (2) deviated splitter vane import blade tip correspondence position, import and export each uniform 8 diffuser pressure gaging hole (9) of position at pneumatic plant back of the body dish (7) diffuser sidewall, along split spiral case (1) circumferential 90 °～360 ° uniform 7 the volute pressure gaging holes of die joint (8), arrange 2 volute pressure gaging holes (8) at aditus laryngis and spiral case outlet simultaneously, arrange 1 volute pressure gaging hole (8) in 30 °～90 ° scopes, whole level amounts to 42 pressure gaging holes.
2, a kind of turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure according to claim 1 is characterized in that: the diameter of described enclosing cover for impeller pressure gaging hole (5), diffuser pressure gaging hole (9) and volute pressure gaging hole (8) is 0.5～1.0mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101431140A CN101545818B (en) | 2009-05-15 | 2009-05-15 | Turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101431140A CN101545818B (en) | 2009-05-15 | 2009-05-15 | Turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101545818A true CN101545818A (en) | 2009-09-30 |
| CN101545818B CN101545818B (en) | 2010-08-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009101431140A Expired - Fee Related CN101545818B (en) | 2009-05-15 | 2009-05-15 | Turbo-charger single-stage prototype centrifugal compressor interstage pressure test structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105571809A (en) * | 2015-12-11 | 2016-05-11 | 中国北方发动机研究所(天津) | Flexibility test device of internal flows of centrifugation compressor |
| CN105822568A (en) * | 2015-01-23 | 2016-08-03 | 哈米尔顿森德斯特兰德公司 | Compressor diffuser and shroud for a motor driven compressor |
| CN111396328A (en) * | 2020-04-30 | 2020-07-10 | 北京动力机械研究所 | A high-efficient centrifugal compressor arrangement for inert mixed working medium |
-
2009
- 2009-05-15 CN CN2009101431140A patent/CN101545818B/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105822568A (en) * | 2015-01-23 | 2016-08-03 | 哈米尔顿森德斯特兰德公司 | Compressor diffuser and shroud for a motor driven compressor |
| CN105822568B (en) * | 2015-01-23 | 2019-06-14 | 哈米尔顿森德斯特兰德公司 | Compressor diffuser and shield for motor driven compressor |
| CN105571809A (en) * | 2015-12-11 | 2016-05-11 | 中国北方发动机研究所(天津) | Flexibility test device of internal flows of centrifugation compressor |
| CN111396328A (en) * | 2020-04-30 | 2020-07-10 | 北京动力机械研究所 | A high-efficient centrifugal compressor arrangement for inert mixed working medium |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101545818B (en) | 2010-08-25 |
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Granted publication date: 20100825 Termination date: 20150515 |
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