RU49188U1 - RING COMBUSTION CAMERA OF A GAS-TURBINE ENGINE - Google Patents

Abstract

The utility model relates to the field of aircraft engine manufacturing, namely, to the design of the combustion chambers of a gas turbine engine (GTE). The annular combustion chamber comprises a housing 1 and a flame tube 2. The housing 1 of the chamber includes an inner 3 and an outer 4 housing interconnected by power struts 5. The struts 5 are installed in the annular diffuser channel formed by these housings (3, 4). , at least a third of the racks 5 are equipped with forks 7 with holes (8, 9) processed according to the conductor. The brackets 11 are welded to the head of the flame tube 2. At the same time, a fuel manifold 25 is inserted into the chamber body 1, onto which additional brackets 26 with eyes 27 are fixed, which are inserted under the forks 7 of the power posts 5. Radial pins 13 are inserted into the holes of the eyes 27 of the additional brackets 26. At the same time, for the radial pins 13, the relation is satisfied: 4≤L / d≤7, where L is the length of the part of the radial pin 13, which is designed to be installed in the holes (8, 9) of the forks 7, eyes 12 of the brackets 11 and eyes 27 additional brackets 26; d is the diameter of the part of the radial pin 13, which is intended for installation in the holes (8, 9) of the forks 7, eyes 12 of the brackets 11 and eyes 27 of the additional brackets 26; The flame tube 2 is made of sections (14, 15, 16, 17, 18, 19). The output sections (16, 19) of the flame tube 2 are provided with support flanges. The supporting flanges are adapted to interface with the rings of the nozzle apparatus 24. The technical result of this utility model is to optimize the mounting structure of the combustion chamber housing and the flame tube while improving the reliability of the combustion chamber. 2 s.p. f-ly, 3 ill.

Description

The utility model relates to the field of aircraft engine manufacturing, namely, to the design of the combustion chambers of a gas turbine engine (GTE).

Known gas turbine engine combustion chamber, which is closest to the claimed utility model, containing a housing in which the power racks are located, and a heat pipe, the inlet end of which is attached to the power racks through forks with holes, brackets with eyes, wound in forks, and radial pins installed in the holes of the forks and eyelets of the brackets [Patent RU No. 2212591 C1, F 23 R 3/60, publ. September 20, 2003].

A disadvantage of the known construction of securing the combustion chamber housing and the flame tube is the wear of the surface of the pins and the surface of the holes on the plug of the power struts of the combustion chamber housing due to the misalignment of the pins and brackets of the flame tube, which reduces the reliability and resource of the combustion chamber.

The technical result of the claimed utility model is to increase the reliability of the mounting structure of the combustion chamber housing and the flame tube while increasing the life of the combustion chamber.

The specified technical result is achieved in that in the annular combustion chamber of a gas turbine engine, comprising a housing and a flame tube, the front of which is attached to the power racks by means of forks with holes, brackets with eyelets inserted into the forks, and radial pins installed in the holes of the forks and eyes brackets, the camera body includes an inner and outer case, interconnected by power racks installed in the annular diffuser channel formed by these cases, not less than

third of the racks are equipped with forks with holes machined according to

conductor, the brackets are welded to the head of the flame tube, while a fuel manifold is inserted into the chamber body, onto which additional brackets with eyes are fixed, which are inserted under the forks of the power struts, radial pins are inserted into the holes of the eyes of the additional brackets, the heat pipe is made sectional, and it the output sections are equipped with support flanges adapted to interface with the rings of the nozzle apparatus rim, moreover, for the radial pins the relation is satisfied: 4≤L / d≤7, where

L is the length of the part of the radial pin, which is intended for installation in the holes of forks, eyelets of brackets and eyes of additional brackets;

d is the diameter of the part of the radial pin, which is intended for installation in the holes of forks, eyelets of brackets and eyes of additional brackets;

The working surfaces of the support flanges must be nitrided, and the outer sections of the flame tube must be connected to the head of the flame tube with rivets.

This technical solution allows you to optimize the design of the combustion chamber. Optimizing the size of the radial pins, along with optimizing the number of racks equipped with forks with holes, increases the reliability of the combustion chamber and eliminates the possibility of the fuel rail brackets coming out of engagement with the pin. Ultimately, this leads to an increase in the resource of the combustion chamber.

The proposed implementation of the output support flanges with the possibility of pairing with the rings of the nozzle apparatus rim, which provides the possibility of radial and axial movement, prevents the deformation of the flame tube, which also affects the increase in reliability and resource of the chamber.

The proposed design allows radial and axial

moving the flame tube, which increases its reliability.

Figure 1 shows a General view of the annular combustion chamber of a gas turbine engine;

Figure 2 is a longitudinal section of a mounting unit of the front of the flame tube and the fuel manifold;

Figure 3 is a longitudinal section of the interface node of the output sections of the flame tube with the rings of the crown of the nozzle apparatus;

The annular combustion chamber of a gas turbine engine (GTE) comprises a housing 1 and a flame tube 2. The housing 1 of the chamber includes an inner 3 and an outer 4 housing interconnected by power struts 5. The struts 5 are installed in an annular diffuser formed by these housings (3, 4) channel 6. At the same time, at least a third of the racks 5 are equipped with forks 7 with holes (8, 9), processed after assembly in the assembly along the conductor. The front part 10 of the flame tube 2 is attached to the power struts 5 by means of forks 7 with holes (8, 9), brackets 11 with eyes 12, which are inserted in the forks 7 and radial pins 13 installed in the holes (8, 9) of the forks 7 and eyes 12 brackets 11. Brackets 11 are welded to the head of the flame tube 2. The bracket 11 is made in such a way that in longitudinal section it has the shape of a triangle, the base of which is attached to the front part 10 of the flame tube 2. The flame tube 2 is made of sections (14, 15, 16 , 17, 18, 19). Sections (15, 16) of the flame tube 2 form an external mixer. Sections (14, 17) and the front part 10 of the flame tube 2 form a head. The output sections (16, 19) of the flame tube 2 are provided with outer and inner support flanges (20, 21). The supporting flanges (20, 21) are configured to mate with the rings (22, 23) of the crown 24 of the nozzle apparatus.

A fuel manifold 25 is introduced into the housing 1 of the chamber, on which additional brackets 26 with eyes 27 are fixed, which are inserted under the forks 7 of the power posts 5. Radial pins 13 are inserted into

the holes of the eyes 27 of the additional brackets 26. In this case, for the radial pins 13, the ratio is: 4≤L / d≤7, where

L is the length of the part of the radial pin, which is intended for installation in the holes of forks, eyelets of brackets and eyes of additional brackets;

d is the diameter of the part of the radial pin, which is intended for installation in the holes of forks, eyelets of brackets and eyes of additional brackets;

This range is due to the fact that when the ratio L / d <4 during operation under the influence of thermal expansions under vibration increases the likelihood of the bracket of the fuel manifold out of engagement with the pin, and when L / d> 7 during operation increases the likelihood of the pin touching the bracket of the fuel collector.

A simple increase in the diameter of the pin d for a fixed length L will lead to the weighting of the entire node, and therefore, to a decrease in the reliability of the combustion chamber.

We give examples of a specific choice of the geometric parameters of the pin.

Example 1: Consider an annular combustion chamber of a gas turbine engine with a pin, the length of which is 64 mm and the diameter is 8 mm.

The length of the part of the radial pin, which is intended for installation in the holes of forks, eyelets of brackets and eyes of additional brackets, is 33 mm (L = 33 mm);

The diameter of the part of the radial pin, which is intended for installation in the holes of forks, eyelets of brackets and eyes of additional brackets, is 8 mm (d = 8 mm);

L / d = 33/8 = 4.1 mm

This value is in the range 4≤L / d≤7.

Example 2: Consider an annular combustion chamber of a gas turbine engine with a pin, the length of which is 80 mm and the diameter d = 8 mm.

The length of the part of the radial pin, which is designed for installation in the holes of forks, eyelets of brackets and eyes of additional brackets, is 57 mm (L = 57 mm);

The diameter of the part of the radial pin, which is designed to install the holes of the forks, eyelets of brackets and eyes of additional brackets, is 8 mm (d = 8 mm);

L / d = 56/8 = 7 mm

This value is in the range 4≤L / d≤7.

Moreover, the working surfaces of the support flanges (20, 21) can be nitrided, and the outer sections (15, 16) of the flame tube 2 can be connected to the head of the flame tube 2 using rivets 28.

A chamfer 29 and a thrust collar 30 are made on the radial pin 13, and a thread 32 is provided on the shank 31 of the radial pin 13. On the camera body 1, bosses 34 are installed in the bosses 33 to protect the radial pins 13 from falling out.

In the process of assembling the combustion chamber, the flame tube 2 is installed inside the housing 1. At the same time, the eyes 12 of the brackets 11 of the flame tube 2 are inserted into the forks 7 of the power racks 5 with a gap in the radial direction. The eyes 12 of the brackets 11 are connected to the forks 7 using radial pins 13, which are inserted through the holes in the bosses 33 on the housing 1 of the combustion chamber. The radial pins 13 are installed using a special key, screwed onto the threaded shank 31. The entrance chamfer 29 on the pins 13 allows them to freely enter the holes of the forks 7, the eyes 12 of the brackets 11 and the eyes 27 of the additional brackets 26. The pins 13 are installed all the way into the shoulder 30. The pins 13 are prevented from falling out by plugs 34 mounted on the bosses 33 of the combustion chamber housing 1.

During engine operation, there is a thermal expansion of the flame tube 2 with the bracket 11, which moves in the radial direction. In this case, the self-centering of the radial pins

in the holes. The supporting flanges (20, 21) of the flame tube 2 can move both axially and radially, compensating for the thermal expansion of the flame tube 2.

This utility model optimizes the design of the combustion chamber. The introduction of the fuel manifold into the camera body, fixing additional brackets with eyes on it, while optimizing the size of the radial pins, as well as optimizing the number of racks equipped with forks with holes, increases the reliability of the combustion chamber and eliminates the possibility of the fuel manifold brackets coming out of engagement with the pin in conditions of vibration and thermal expansion.

Claims (3)

1. An annular combustion chamber of a gas turbine engine, comprising a housing and a flame tube, the front part of which is attached to power racks by means of forks with holes, brackets with lugs inserted into the forks, and radial pins installed in the holes of the forks and eyelets of the brackets, characterized in that the camera housing includes inner and outer housings interconnected by power racks installed in the annular diffuser channel formed by these housings, at least a third of the racks are equipped with forks with The holes machined by the conductor, the brackets are welded to the head of the flame tube, while the fuel manifold is inserted into the chamber body, on which additional brackets with eyes are fixed, which are inserted under the forks of the power racks, radial pins are inserted into the holes of the eyes of the additional brackets, the heat pipe is made sectional , and its output sections are equipped with support flanges, made with the possibility of interfacing with the rings of the crown of the nozzle apparatus, and for the radial pins the ratio is: 4≤L / d≤7 where L is the length of the part of the radial pin, which is intended for installation in the holes of forks, eyelets of brackets and eyes of additional brackets; d is the diameter of the part of the radial pin, which is intended for installation in the holes of forks, eyelets of brackets and eyes of additional brackets; 2. The annular combustion chamber of a gas turbine engine according to claim 1, characterized in that the working surfaces of the support flanges are nitrided. 3. The annular combustion chamber of a gas turbine engine according to claim 1, characterized in that the outer sections of the flame tube are connected to the head of the flame tube with rivets.