RU2267030C1 - Gas-turbine engine axial-flow compressor stage - Google Patents

Abstract

FIELD: mechanical engineering.

SUBSTANCE: invention can be used in members of rotor of compressors of gas-turbine engines, namely, in blade fastening units. According to invention, stage of axial-flow compressor of gas-turbine engine is provided with blade rims of impeller and ring band made in form of support load-bearing ring whose outer part is made of composition material and inner part, of metal. Inner metal ring is provided with splines for fastening roots of blade tail section by means of webs with mating splines.

EFFECT: improved reliability of lock.

2 dwg

Description

The invention relates to mechanical engineering, namely to turbomachines, for example, to axial compressors of gas turbine engines (GTE) with wide chord blades or blades with a large twist.

Modern gas-turbine engines use wide-chordate blades, as well as blades with large twist angles, in which, in addition to stresses from centrifugal forces, significant torsional and bending stresses arise. Under these conditions, it is necessary to prevent them from twisting and deforming along the chord along the entire length of the blade, to ensure good aerodynamic characteristics and to prevent resonant vibrations.

Known stage axial compressor GTE, described in patent for invention No. 2211381, class. F 04 D 29/34, published August 27, 2003, bull. No. 24, adopted for the prototype, having the impeller crowns and an annular bandage, the latter being made in the form of an external support ring for the shanks of the end section of the blades, which are mounted in it with a dovetail trapezoidal lock, for which the inner surface of the support the rings are made of metal and has grooves.

The disadvantage of this design is that the fastening of chordate blades or blades with a large twist in dovetail locks is impossible, the locks have a large mass and a small contact area with the power ring.

In addition, when the blade is broken, a centrifugal force that is close to concentrated due to the small area and large mass of the lock will act on the external power ring.

An object of the invention is to increase the reliability of the design of the lock, fastening broad-chordate blades or blades with a large twist, reducing the thickness and mass of the ring.

The solution to the technical problem lies in the fact that in the stage of the axial compressor of the gas turbine engine, containing the impeller blades and an annular bandage, the latter being made in the form of an external support ring for the shanks of the blade end section, for fixing the shanks of the blade end section on the inner surface of the metal ring at least two slots, and a shelf that is provided with reciprocal slots is fixed on the shank of the end section of the blade.

The technical result of the claimed invention lies in the fact that the improvement of the prototype will allow to install wide-chord blades and blades with a large twist in the design. This will reduce the thickness of the power ring and, accordingly, the mass, evenly distribute the load on it during the construction operation and in case of blade breakage, reduce the lock loads from torsion of the blade by increasing the shoulder, and secure the end part of the blade with a spline connection with the entire profile by means of a shelf fixed to the shank end section of the scapula.

Salient features of the claimed invention are the following elements of the device:

- slots made on the metal surface of the support power ring for mounting the shanks of the end section of the blades;

- a shelf with reciprocal slots, mounted on the shank of the end section of the scapula;

In Fig.1 is a drawing of a General view of the stage of the axial compressor of the gas turbine engine, in Fig.2 - section aa in Fig.1.

Description of the device.

The stage of the axial compressor of the gas turbine engine consists of a disk 1 on which the root shanks 2 of the blade feather 3 are attached using a trapezoidal lock. In the peripheral part of the impeller there is an annular bandage in the form of an external support power ring, the outer part 4 of which is made of composite material, and the inner part 5 is metal, equipped with slots 6. For fastening the shanks 9 of the end section of the blades 3, the shanks are equipped with shelves 7 with reciprocal slots 8.

When the compressor is operating, the slots on the inner metal part of the external supporting power ring, which are connected to the mating slots on the flange of the shank of the end section of the blade, ensure the reliability of fastening wide-chord blades or blades with a large twist, structural rigidity, uniform distribution of load on the ring, reduction of the level of vibration stresses in blades, and consequently, an increase in their resource, a decrease in the thickness of the ring and its mass.

Sources of information

1. Patent for invention No. 2211381, class. F 04 D 29/34, published August 27, 2003, bull. No. 24 (prototype).

Claims (1)

The stage of the axial compressor of a gas turbine engine containing the impeller crowns and an annular bandage, the latter being made in the form of an external support power ring for attaching shanks of the end section of the blades that are mounted in it, for which the inner surface of the support power ring is made of metal, characterized in that for fastening the shanks of the end section of the blade on the inner metal surface of the power ring, slots are made, and on the shank of the end section of the blade ki fixed shelf, which is provided with complementary splines.

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