Gas turbine stator

Abstract

The invention is related to the gas turbine stators of the gas turbine engines applied in aviation. The gas turbine stator, in the outer housing of which sectors of the split honeycomb ring (made as double-layer one) are installed with support elements on the front and rear axial ends of the sector. In this invention, the layer of the sector facing the outer housing is made U-shaped in the plane, the support elements are made as separate rotary bodies distributed uniformly along the circumference and the front support elements (on the gas flow direction) are larger than rear ones in terms of geometrical dimensions by factor 1.1 . . . 1.5. Therefore, the implementation of the invention proposed with the characteristic features above, in conjunction with the known features of the invention claimed enables reduction of the gas turbine stator weight and improvement its reliability without compromising the turbine efficiency.

Claims

1. A gas turbine stator in an outer housing of which sectors of a split honeycomb ring are installed; the split honeycomb ring is made as a double-layer, with support elements on front and rear axial ends of the sectors characterized in the fact that a layer of the sectors facing the housing is made U-shaped in a plane, the support elements are made as separate rotary bodies distributed uniformly along a circumference defined by the sectors and the support elements on the front axial end are larger than the support elements on the rear axial end in terms of geometrical dimensions by factor 1.1 . . . 1.5.

2. Gas turbine stator as per claim 1 characterized in the fact that the support elements are made as truncated cones.

Description

BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWINGS

(1) FIG. 1 shows longitudinal cross-section of the gas turbine stator;

(2) FIG. 2 shows View A of FIG. 1;

(3) FIG. 3—View B of FIG. 1;

(4) FIG. 4—View C of FIG. 2.

DETAILED DESCRIPTION OF THE INVENTION

(5) Stator 1 of the gas turbine includes outer housing 2 in which sectors 6 of the split honeycomb ring 7 are installed between the front 3 and rear 4 nozzle blades along the gas 5 stream. Sectors 6 are made of metal sheets in two layers, with the inner layer 8 solid and the outer layer 9 facing the outer housing 2 is made U-shaped in the plane. On the front 10 and rear 11 ends of the sector 6 front 12 and rear 13 support elements made as rotation bodies (for example, truncated cones) located uniformly along the circumference are installed. The front support elements 12 lock the lock ring 14 against radial displacement for which reason they are made 1.1 . . . 1.5 times larger (in terms of the geometric dimensions) than the rear support elements 13 which take up the load only of the sector 6 itself. The geometric similarity of the support elements 12 and 13 enables their fabrication cost reduction.

(6) This device operates as follows.

(7) During the operation the high-temperature gas stream 5 flows inside the stator 1 of the gas turbine; in case of the contact with the stream the outer housing 2 of the stator 1 could be damaged. However, it does not occur because sectors 6 of the split honeycomb ring 7 reliably prevent the outer housing 2 from the contact with the gas stream 5 at the minimum weight of the sectors 6. Hereby, the front 10 and rear 11 ends of the sector 6 are double-layered and with the front and rear support elements 12 and 13 which improves the reliability of locking of the sectors 6 in the front and rear nozzle blades 3 and 4.

(8) Therefore, the implementation of the proposed invention with the characteristic features above, in conjunction with the known features of the invention claimed enable reducing the weight of the stator of the gas turbine and improving the reliability without compromising the turbine efficiency.