SU1036121A1 - Combustion chamber of gas turbine engine - Google Patents

Abstract

COMBUSTION CHAMBER OF A GAS TURBINE ENGINE, containing a heat pipe installed in the housing with the formation of an annular channel with annular rows of secondary openings and WG L; G; g:;.: i ..- .h ;:, fciJ7fii4 of mixing air and a front-end device, at the entrance to which an annular collector connected to a compressed air source with openings directed at an angle to the chamber axis against flow, lt. Due to the fact that, in order to ensure complete combustion and reliability of operation, the casing and heat pipe are provided with additional headers, installed respectively at the entrance to the annular channel and at each row of holes, and the bushings are installed in the holes, the collector of the Boij-o channel has open the a each flame tube collector is an annular gap directed, respectively, at an angle to the axis of the chamber and at an angle to the axis of the sleeve against the flow. WITH Gb

Description

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This invention relates to a gas turbine.

A combustion chamber of a gas turbine engine is known, including a heat pipe installed in the housing. An annular damper is connected to the side of the shell, overlapping with the movement of the aperture of the secondary and mixing air t

The core of such a chamber is large hydraulic losses due to the introduction of the damper and drive elements into the air flow, as well as the violation of the optimal shape of the holes when they are blocked by the damper. The combustion chamber of the gas turbine engine containing the annular channel is closest to the invention a flame tube with rings of a series of openings of the secondary and mixing air and a front-end device, at the entrance to which is located connected to the compressed air source of the rings apertured manifold minutes mij directed at an angle to the axis of the chamber 2J against stream.

However, in such a chamber, the presence of a regulating air flow rate of the collector only at the entrance to the front-mounted device does not provide high completeness of combustion and reliability in the entire range of engine operating modes.

The aim of the invention is to improve the completeness of combustion and reliability of operation.

This goal is achieved by the fact that the combustion chamber of a gas turbine engine contains a heat pipe installed in the housing to form an annular channel with annular rows of secondary and mixing air openings and a front device at the entrance to which an annular manifold connected to the compressed air source is located. mi directed at an angle to the chamber axis upstream, the casing and the flame tube are equipped with additional headers installed respectively at the entrance to the annular channel and at each rows of apertures. Plugs are installed in the holes, the annular channel collector has grazes, and each flame tube collector has an annular gap directed respectively at an angle to the chamber axis and at an angle to the axis of the sleeve against the flow.

one

FIG. 1 schematically shows a combustion chamber, a longitudinal section; in fig. 2 — node I of FIG. one.

A casing tube 2 is installed in the housing 1, having a front-mounted device 3, annular rows of holes 4 and an annular channel 5 forming the casing 1. At the exit to the front-mounted device 3 there is a ring collector 6 connected to a source of compressed air 7, holes 8 are made on the collector directed at an angle to the axis of the camera towards the flow. The housing 1 also has a collector 9 connected to a source of compressed air 7 and having openings 10 directed at an angle to the chamber axis against the flow. A collector 11 is located in each row of openings 4 in the flame tube 2. each collector 11 is provided with an annular gap TZ, directed at an angle to the axis of the sleeve 12 against the air flow in it. The source 7 of compressed air communicates with the manifolds 6, 9 and 11 by pipelines 14, in which solenoid valves 15 are installed. Holes 8, 10 and slot 13 are directed against the flow at an angle of 90-160s (preferably 135 ° C). Holes B and 10 may be shaped as slots.

When the combustion chamber is operated in the prescribed mode, the solenoid valves 15 are opened, and additional air is supplied to the manifolds 6, 9 11 through pipelines 14 from the source 7. Blowing additional air through the holes 8, 10 and the slot 13 at an angle of 90-160 ° against the air flow in the front device 3, the annular channel 5 and in the holes 4 of the sleeves 12 creates local flow resistance and provides control of primary, secondary and mixing air flow pipe length 2. When changing the mode of operation of the combustion chamber, the channels 15 redistribute the air flow through the manifolds 6, 9 and 11, maintaining an optimal air supply along the length of the flame tube in the new mode. i

Such an embodiment of the combustion chamber ensures its reliable operation with a high completeness of combustion in the entire range of operating modes and reduces the hydraulic losses in the chamber.

Claims (1)

COMBUSTION CAMERA OF A GAS TURBINE ENGINE, comprising a heat pipe installed in the housing with the formation of an annular channel, with annular rows of secondary and mixing air openings and a frontal device, at the inlet of which there is an annular manifold connected to a compressed air source with openings directed at an angle to the chamber axis against the flow , kicking by the fact that, in order to increase the completeness of combustion and reliability of operation, the casing and the flame tube are equipped with additional collectors, installed accordingly venno inlet into the annular channel and each row of holes, the holes in the sleeve mounted, annular manifold channel has holes, and each flame tube collector - annular slot, directed, respectively, at an angle to the camera axis at an angle to the axis of the sleeve against the flow. >