SU1466358A1 - Gas turbine blade - Google Patents

Abstract

The invention relates to power engineering and m. B. used in gas turbine installations. The invention makes it possible to increase the life by increasing the cooling efficiency. On the inner surface of the pen, there are 2 protrusions 8 of protrusions with plp 9. R groove 9 of the protrusion 8 spaced in the in-zone edge and groove, with their longitudinal edges / FTP / K collector 3. PR 1 are installed in grooves 9 with slot gaps / SCH / S between the stich pen and the ends of the OL Ki. HGs 5 are located with W 3 in the slots 9 of the remaining protrusions 8 with образ-shaped memory and compartments inside the pen. Near the wall of the pen 2, the visors 12 of the partition 5 are bent at an acute angle above Ø 3. When cooling works, air enters the cavity of pen 2 through manifold 3, passes through compartments 7 and is removed from the blade through the opening of the exit edge 1. When air flows from the compartment In the compartment, additional feather cooling is provided by 2 wall air jets emanating from W 3. 3. 1 h. the item of f-ly, 4 ill. . i (L

Description

The invention relates to power engineering and can be widely used in cooled turbine blades of gas turbine plants. I

The aim of the invention is to increase the resource by increasing the cooling efficiency.

Figure 1 shows the blade, a longitudinal section in Fig, 2 - section aa in figure 1; on FIG. 3 — section B — B in FIG. 2, in FIG. 4 — prodig1, a protrusion with a palom and a parapet with a visor.

A gas turbine blade with a Bi.tnyc-cooling air Cheroz to the exit edge 1 contains a floor pen 2 and a collector 3 located on it, located in the zone of the entrance edge 4, longitudinal perforated partitions 5 with holes 6 forming the compartments 7, On the inside

The surfaces of the pen 2 are longitudinal protrusions 8 with grooves 9, which have partitions 3 installed with a gap of 10 Mfwiy with a feather grip 2 and an end face 11 psgol ,, l1a 5. Partitions 5 have cncrc 12.

CD O5 00 SL

00

The collector 3 is made in a pid perforated from the side of the input edge of the tube with longitudinal ribs 14 located in the grooves 9 of the projections 8 of the pen 2 with a slotted gap between its wall and the end 15 of the ribs 14.

Near the wall of the pen 2, the visors 12 of the partition 5 are bent at an angle above the slotted gap Yu between the wall of the pen 2 and the end 11 of the partition.

During operation, the cooling air enters the co / chector 3, flows out of its openings and, due to the impact of the jets, cools the surface of the inlet edge 4, then two flows along the concave and convex surface of the pen 2 afterwards passes through the compartments 7 and is removed from the blade output edge holes 1.

At the transition of air from the compartment to the compartment, an intensive additional cooling of the pen 2 by wall air jets, the flow of air from the slits of the gaps 10, is provided.

In this case, the temperature of the rtoe field of the pen blade is reduced;

thermal stresses, the cyclic durability of the blades on the modes of recruitment and discharge of power increases, which leads to an increase in the resource life of the blades of a gas turbine.

Claims (2)

1. A gas turbine blade containing a hollow feather and longitudinal perforated partitions located therein and a collector located in the zone of the inlet edge and having a casing with the last hole, characterized in that, in order to increase the cooling efficiency, the collector has with the ribs, and the feather on the inner side with longitudinal ridges with grooves, the partitions and the ribs being placed in the grooves with slit gaps. 2. A blade according to claim 1, characterized in that the partitions are provided with goats, located above the slit gaps. (pic 2 , 8, 10 -ff 5 -ff gjua3 ff