RU2810187C1 - Flame stabilizer of afterburner of gas turbine engine - Google Patents

Abstract

FIELD: aviation gas turbine engines.

SUBSTANCE: invention relates in particular to afterburners for turbojet engines, including flame stabilizers manufactured by casting or selective laser melting. The flame stabilizer of the afterburner chamber of a gas turbine engine contains stabilizers made in a T-shape, which are subsequently assembled into a ring, radial and ring carburetors made by casting or selective laser fusion. The carburetors are fixed at two points, while in the area of the air intakes they are stationary, and the second point of attachment to the stabilizer is made floating to compensate for the difference in temperature expansion of materials by making oval holes in the stabilizer and fastening the carburetors in them using pins permanently attached to the carburetors and rings, attached to the pins, but without attachment points to the stabilizer.

EFFECT: providing compensation for temperature expansions (temperature decoupling) between the stabilizer and carburetors, the ability to replace carburetors without replacing the stabilizer to ensure maintainability, as well as to ensure easy repair of the afterburner (front device) by quickly replacing the stabilizer.

1 cl, 5 dwg

Description

The invention relates to the field of aviation gas turbine engines, in particular to afterburners for turbojet engines, including flame stabilizers manufactured by casting or selective laser melting.

The design of a flame stabilizer used in the afterburner chamber of a gas turbine engine is known (A.A. Inozemtsev, V.L. Sandratsky “Gas Turbine Engines”, JSC “Aviadvigatel”, Perm, 2006, pp. 356-360), in which the carburetor and stabilizer are one piece.

The disadvantage of this design is that it is not designed to work as part of a 5th generation engine, since it does not provide temperature isolation between the carburetor and the stabilizer, which leads to the formation of cracks and disruption of the afterburner chamber.

The purpose of the invention is to provide compensation for temperature expansions (temperature decoupling) between the stabilizer and carburetors, the ability to replace carburetors without replacing the stabilizer to ensure maintainability, as well as to ensure easy repair of the afterburner (front device) by quickly replacing the stabilizer.

In order to increase strength and achieve a given resource, a design of a prefabricated flame stabilizer is proposed, consisting of a stabilizer, radial and ring carburetors, made by casting or selective laser melting, the distinctive feature of which is the design and assembly method, which provides compensation for temperature expansion between the stabilizer and carburetors.

This purpose of the invention is achieved by the fact that the flame stabilizer of the afterburner chamber of a gas turbine engine contains stabilizers made in a T-shape, which are subsequently assembled into a ring, radial and ring carburetors made by casting or selective laser fusion. The carburetors are fixed at two points, while in the area of the air intakes they are stationary, and the second point of attachment to the stabilizer is made floating to compensate for the difference in temperature expansion of materials by making oval holes in the stabilizer and fastening the carburetors in them using fingers fixedly fixed to the carburetors and rings, attached to the fingers, but without attachment points to the stabilizer.

Fig. 1 - general front view of the stabilizer

Fig. 2 - general view of the rear stabilizer

Fig. 3 - section of the carburetor mounting location

Fig. 4 - carburetor mounting location

Fig. 5 - layout diagram of stabilizers in the afterburner chamber,

On the drawings

1. T-shape stabilizer

2. radial carburetor

3. ring carburetor

4. air intake

5. finger

6. ring.

The stabilizer is shown in Fig. 1.2 and consists of a T-shaped stabilizer 1, made by casting or selective laser fusion, carburetors: radial 2 and ring 3, also made by casting or selective laser fusion, fingers 5 and rings 6.

Carburetors 2 and 3 are attached on one side to the stabilizer 1 rigidly with rivets from the side of the air intakes 4 and on the other side - using pins 5 and rings 6, while this connection is floating to compensate for the temperature stresses that arise in the material during engine operation. Pins 5 are attached to carburetors 2 and 3 by welding.

In fig. Figure 3 shows a cross-section of the stabilizer at the attachment point, where pin 5 and ring 6 are shown; the same place is shown large in Fig. 4. In FIG. 3.4 you can see the hole in the stabilizer, which is made oval to allow movement of the finger 5, which compensates for the different temperature movements of the materials from which the stabilizer 1 and carburetors 2 and 3 are made, since during operation they heat up to different temperatures.

Flame stabilizers (assembled) are installed in the afterburner according to the diagram shown in Fig. 5 in such a way that the annular parts of the stabilizers form a ring and form a flame stabilization system. In the flame stabilization system of the afterburner of the gas turbine engine of the front unit, a zone of reverse currents is created, which ensures complete fuel combustion, reliable starting and stable operation of the afterburner in a wide range of modes.

The advantages of the proposed design include:

1. Small volume of parts processing, since a workpiece grown by selective laser melting or a casting practically represents a finished part;

2. Compensation of temperature stresses between the stabilizer and carburetors.

The gas turbine engine afterburner flame stabilizer is used in the design of aircraft gas turbine engines with an afterburner combustion chamber.

Claims (1)

Flame stabilizer of the afterburner chamber of a gas turbine engine, containing T-shaped stabilizers, which are subsequently assembled into a ring, radial and ring carburetors made by casting or selective laser fusion, characterized in that the carburetors are fixed at two points, in the area of the air intakes stationary, and the second attachment point to the stabilizer is made floating to compensate for the difference in temperature expansion of materials by making oval holes in the stabilizer and attaching carburetors in them using fingers fixedly fixed to the carburetors and rings attached to the fingers, but not having points of attachment to the stabilizer .