SU595520A1 - Moving blade of axial-flow turbine machine - Google Patents

Description

The invention relates to the field of power engineering and can be found in the compressor room and the torostroiin valve.

A known working axial axial turbomachine, on which plates are installed, having a height in accordance with the height of the lower limiting layer and nanaraple along the streamline 1.

Odiako installation of power} eliminates the rotation of the blades, and consequently, on the aerodynamic regular adjustment of the mangnans.

The closest to the invention is a technical blade of the well-known working blade of an axial turbomachine, which is designed by a crankcaseor, with a profile, the spine of which is made with non-ribs, heated with a perforated and sleeve part of the nrofil. Moreover, the edges are located on the current 2.

The design of the blade allows it to rotate, but the performance of the ribs in terms of current is of little effect.

The purpose of the invention is to improve aerial characteristics by preventing flow disruption.

It is achieved that each edge is matched with a radus profile equal to the height of the rib, n from the periphery and bushings

The rib edge is located on a set of mon x, respectively determined by the formulas: 5, - / ;, - al-,

5,: - - OL-,

where / g; - distance from profile periphery to

edges of the entrance edge of the blade; / 72 - distance from profpl to

edges at the entrance edge of the lap; “- coefficient equal to 0.06-0.09;

b is a coefficient equal to 0.09-0.15; X - current raestho npe from the entrance edge.

FIG. 1 shows the proposed blade, front in front; pas figs. 2 - cut. pas figs. i.

Working blade 11 has nrofpl 1, on the screenshot 2 of which non-ribs 3 are made,

4, located on the periphery and the stub part of the nfnl 1, each edge

3 and 4 are matched with a profile with radius Rt, R2,

equal to the height L.,., ribs, n from the periphery 5

and 6 nrofnl ribs 3, 4 are open;

at distances x, Si, 2, respectively, determined by the form; ulam;

five, ; ; / ;, -ad-, 5, - /; "- bх,

Such an embodiment of the ribs on the base of professional blades improves the shape of the pressure curves, and IIIH increases proi iedity as during direct work, as well as in reverse. As a result of the development, the ecuperimepts, the 11th-1-asma blade of the turbo-marshpy poses the efficiency by 3–3.5%, and the proi: io lte, 1) Go with revoer by 8 --- 10%.

F o rm u l a p 3 o 5 () e te of e and u

The working blade axial turbomapipiz, has the advantage of the compressor. The profile of the transverse ribs, which are paired with a perforated and sleeve-shaped part of the profile, is characterized by the fact that, in order to improve the airfield, we need it; cell characteristics by means of a pre-flow flow, each edge is smoothly equipped with a radus profile, a rib height, and a rib profile from the periphery of the sleeve b

-B.-: //, -i.V,

i, u: / m - I ;;;; T; - ;;;; ;; i; e from perperferpi profile to rsboa in () DPS} 11 edge blades;

 ; asst:) IP1; e from a profile to reoz: (edge of a shovel;

:; (l;: jiiii: .aii; pbB, i:., iM 0.06H - 0.09;

& - - Koef (i1tsps11t, 0,094-0.15;

.V - 1c-ku:; its distance (y; - doddop kromkp.

 cT04iii: Kii 1; 1 formations accepted in the BniiMaiine prn examination

1. Patent S1PA L o039736, cl. 416-90,

OP.b .: 1962.

2.Lv10; Kko svpdete.stvo SS; CP 79882,; -; l. F 04f 29/38, 1948.

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