CN104564841A

CN104564841A - End bending joint bending static blade of multistage axial flow compressor

Info

Publication number: CN104564841A
Application number: CN201410850144.6A
Authority: CN
Inventors: 张成义; 王松涛; 张春梅; 李秉安; 冯永志; 杜鑫; 秦华魂; 赵俊明; 周驰
Original assignee: Harbin Turbine Co Ltd
Current assignee: Harbin Turbine Co Ltd
Priority date: 2014-12-30
Filing date: 2014-12-30
Publication date: 2015-04-29

Abstract

The invention discloses an end bending joint bending static blade of a multistage axial flow compressor and relates to an end bending joint bending static blade, and in particular relates to an end bending joint bending static blade of the multistage axial flow compressor. The end bending joint bending static blade of the multistage axial flow compressor solves the problems of the existing multistage axial flow compressor that the positive attack angle at the near end wall is gradually increased along the increase of load of the rear stage static blade, the compressor turns into the stall condition ahead of time and the work stability of the compressor is poor. The end bending joint bending static blade of the multistage axial flow compressor comprises a static blade main body, the root of the static blade main body is provided with an end bending blade region, the lower part of the static blade main body is provided with bending blade region, the end bending blade region has end bending along the track of the blade type front edge dot product idea line, the end bending height h1 of the end bending blade region is 0-12% of the height L of the blade, the bending blade region bends along the track of the blade center of mass product pile shaft, the bending height h2 of the bending blade region is 88-100% of the height L of the blade. The end bending joint bending static blade is used for the compressor.

Description

A kind of for the curved stator blade of the curved associating of the end in multi stage axial flow compressor

Technical field

The present invention relates to the curved stator blade of the curved associating of a kind of end, be specifically related to a kind of for the curved stator blade of the curved associating of the end in multi stage axial flow compressor.

Background technique

The later stages stator blade petiolarea of existing multi stage axial flow compressor easily causes the flow separation of large scale because of boundary layer accumulation, petiolarea through-current capability reduces, and makes gas compressor enter stall operating mode ahead of time, reduces compressor efficiency and total pressure ratio.

Summary of the invention

The present invention is the later stages stator blade that solves existing multi stage axial flow compressor along with load increases, the positive incidence at proximal end wall place increases gradually, gas compressor is made to enter stall operating mode ahead of time, the problem of the poor work stability of gas compressor, and then propose a kind of for the curved stator blade of the curved associating of the end in multi stage axial flow compressor.

The present invention is the technological scheme taked that solves the problem: the present invention includes stator blade main body, the root of stator blade main body is provided with end bent blades district, the bottom of stator blade main body is provided with bent blades district, end bent blades district changes along blade profile leading edge dot product, and to carry out end curved for the track of line, the curved height h1 of end in end bent blades district is 0% ~ 12% of blade height L, the track that bent blades district amasss folded axle along vane centroid bends, and the bending height h2 in bent blades district is 88% ~ 100% of blade height L.

The invention has the beneficial effects as follows: 1. the present invention only carries out holding curved technology to retrofit for the later stages stator blade upper end wall of multi stage axial flow compressor and lower end wall and bent blades is retrofited respectively, obtain the curved associating bent blades of end, negative influence can not be produced to the aspect such as blade strength, vibration of gas compressor entirety; Meanwhile, the present invention adopts spline curve curved surface to carry out blade forming, blade profile fairing.2. the present invention is according to mass conservation law and principle of conservation of momentum, by holding the curved remodeling of curved associating to stator blade, single-stage compressor pressure ratio is made to improve 1%, the isentropic efficiency of single-stage compressor adds 1.5% before not retrofiting, effectively can also suppress the flow separation of petiolarea, make the inflow of air-flow and flow out the blade profile curve of blade of more fitting, with the angle automatching in gas compressor main flow region, improving the working stability of gas compressor.The present invention is mainly used in multistage compressor, due to the cumulative effect of the upper and lower end-wall boundary layer of previous stages, easily there is flow separation comparatively greatly in the thicker high scope of leaf that accounts for of later stages import petiolarea boundary layer, simultaneously because the separation of stator blade mainly concentrates in the angular region of casing surface and suction surface formation, therefore adopt end curved to 0% ~ 12% place apart from blade profile root blade height.Before calculating 40% chord length in a large number, the boundary layer loss in end bent blades is less, and much smaller than the positively curved blade that bent angle is identical, after 40% chord length, the positively curved blade that the control ability that end bent blades diagonal regions is separated is but identical with bent angle is suitable.Therefore, on the basis of end bent blades, the curved associating bent blades technology of end is adopted can to obtain the blade with lower loss.Choose optimal case by numerical simulation calculation and determine that the import geometry angle of its root increases the scope of 0 ~ 10 ° and the scope of bend angle 0 ~ 40 °.

Accompanying drawing explanation

Fig. 1 is plan view of the present invention, and Fig. 2 is the curved schematic diagram of end of end bent blades of the present invention, and Fig. 3 is the bending schematic diagram of bent blades.

Embodiment

Embodiment one: composition graphs 1 to Fig. 3 illustrates present embodiment, a kind ofly described in present embodiment comprise stator blade main body 1 for the curved stator blade of the curved associating of the end in multi stage axial flow compressor, the root of stator blade main body 1 is provided with end bent blades district 3, the bottom of stator blade main body 1 is provided with bent blades district 4, end bent blades district 3 changes along blade profile leading edge dot product, and to carry out end curved for the track of line 2, the curved height h1 of end in end bent blades district 3 is 0% ~ 12% of blade height L, the track that bent blades district 4 amasss folded axle 5 along vane centroid bends, the bending height h2 in bent blades district 4 is 88% ~ 100% of blade height L.

Embodiment two: composition graphs 1 to Fig. 3 illustrates present embodiment, described in present embodiment, a kind of import geometry angle α 2 of end bent blades 7 blade profile of the end bent blades district 3 for the curved stator blade of the curved associating of the end in multi stage axial flow compressor increases α compared with the initial import geometry angle α 1 of prototype blade 6, α=0 ~ 10 °, under the condition that inlet flow conditions is constant, reduce the air inlet angle of attack.Other composition and annexation identical with embodiment one.

Embodiment three: composition graphs 1 to Fig. 3 illustrates present embodiment, described in present embodiment, a kind of bent blades of the stator blade main body 1 for the curved stator blade of the curved associating of the end in multi stage axial flow compressor gets the lower end blade profile bend angle γ of 4 is 0 ° ~ 40 °, and to blade suction surface lateral bend.Other composition and annexation identical with embodiment one.

Claims

1. one kind for the curved stator blade of the curved associating of the end in multi stage axial flow compressor, it is characterized in that: describedly a kind ofly comprise stator blade main body (1) for the curved stator blade of the curved associating of the end in multi stage axial flow compressor, the root of stator blade main body (1) is provided with end bent blades district (3), the bottom of stator blade main body (1) is provided with bent blades district (4), end bent blades district (3) changes along blade profile leading edge dot product, and to carry out end curved for the track of line (2), the curved height h1 of end of end bent blades district (3) is 0% ~ 12% of blade height L, bent blades district (4) bends along the track of the long-pending folded axle (5) of vane centroid, the bending height h2 in bent blades district (4) is 88% ~ 100% of blade height L.

2. a kind of for the curved stator blade of the curved associating of the end in multi stage axial flow compressor according to claim 1, it is characterized in that: the initial import geometry angle α 1 of the import geometry angle α 2 comparatively prototype blade (6) of end bent blades (7) blade profile of end bent blades district (3) increases α, α=0 ~ 10 °, under the condition that inlet flow conditions is constant, reduce the air inlet angle of attack.

3. a kind of for the curved stator blade of the curved associating of the end in multi stage axial flow compressor according to claim 1, it is characterized in that: the lower end blade profile bend angle γ that the bent blades of stator blade main body (1) gets (4) is 0 ° ~ 40 °, and to blade suction surface lateral bend.