RU161141U1 - TWO-CIRCUIT GAS-TURBINE ENGINE - Google Patents

Abstract

1. A double-circuit gas turbine engine containing a turbine with blades, an afterburner with a diffuser with outer and inner walls interconnected, and a nozzle, characterized in that the diffuser is made cooled, the inner wall of the diffuser is double with a channel, while the walls of the diffuser are connected hollow cooled pylons, which are made with concave and convex walls. 2. The dual-circuit gas turbine engine according to claim 1, characterized in that the walls of the diffuser and the concave walls of the pylons are made with holes.

Description

The utility model relates to aircraft engine building, in particular, to dual-circuit gas turbine engines with afterburner and can be used to reduce the visibility of aircraft in the infrared range.

A two-circuit gas turbine engine is known, comprising a turbine with blades, a turbine cowl with cooled and uncooled parts and an afterburner with ring flame stabilizers, while the small ring flame stabilizer is made cooled and is installed so that it obscures (shields) the uncooled part of the turbine cowling from the nozzle side which reduces infrared visibility during engine operation (See patent RU No. 2480604, CL. F02K 3/02, publ. 04/27/2013).

A disadvantage of the known engine is the low efficiency of reducing the infrared visibility of the aircraft, since it does not provide shielding from all angles of the uncooled part of the turbine cowl and other heated engine parts, in particular, turbine blades.

The technical result of the claimed utility model is to reduce the visibility of the aircraft in the infrared range.

The specified technical result is achieved in that in a double-circuit gas turbine engine containing a turbine with blades, an afterburner with a diffuser with outer and inner walls interconnected, and the nozzle, diffuser are made cooled, the inner wall of the diffuser is double with a channel, while the walls of the diffuser connected by hollow cooled pylons, which are made with concave and convex walls.

The specified technical result is enhanced when the walls of the diffuser and the concave walls of the pylons are made with holes.

In FIG. 1 schematically shows a dual-circuit gas turbine engine with a mixture of working fluid flows and a common afterburner;

in FIG. 2 shows a afterburner diffuser with engine pylons (longitudinal section);

in FIG. 3 shows a view A along the arrow in FIG. 2.

The gas turbine engine contains an inner circuit 1 and an outer circuit 2, a turbine with rotor blades 3, an afterburner with a diffuser. An annular diffuser is formed by the separating contours 1 and 2 of the outer wall 4 and forming the turbine coke inner wall 5.

The walls 4 and 5 of the diffuser are interconnected by hollow profiled cooled pylons 6. To cool the diffuser, its walls 4 and 5 are made with holes 7 and 8, respectively. Each pylon 6 has a concave wall 9 with holes 10 and a convex wall 11, a cavity 12 and holes 13 in the output edge. The implementation of the pylons 6 cooled with concave and convex walls allows for shielding (blocking) the visibility of the turbine blades from the nozzle side. That is, the pylons 6 perform the function of a protective screen.

Pylons 6 form a lattice of profiles, straightening the flow exiting from the impeller of the low pressure turbine. The shape of the pylons, their number, the location in the diffuser (along the entire length of the diffuser or in part) and the perforation area are selected depending on the engine parameters. For more efficient cooling, the inner wall 5 of the diffuser is made double with a channel 14.

Also shown in the drawings: 15 - turbine coke, 16 - afterburner, 17 - nozzle.

The operation of the gas turbine engine is as follows.

Air from the outer circuit 2 enters through an opening (not shown) in the outer wall 4 of the diffuser into the cavity 12 of each pylon 6. Next, part of the air flow exits through the openings 10 and 13 into the flowing part of the inner circuit 1, forming an air curtain, cools the concave side wall 9 pylons 6 and their output edge. Another part of the flow from the cavity 12 enters the channel 14 and then enters the flowing part of the internal circuit through the openings 8, forming an air curtain, and cools the inner wall 5 of the diffuser. The outer wall of the diffuser 4 is cooled by air flowing along the outer circuit 2 and forming an air curtain, due to the presence of holes 7.

Thus, the proposed solution by shielding and cooling hot engine parts, reduces the visibility of the aircraft in the infrared range.

Claims (2)

1. A double-circuit gas turbine engine containing a turbine with blades, an afterburner with a diffuser with outer and inner walls interconnected, and a nozzle, characterized in that the diffuser is made cooled, the inner wall of the diffuser is double with a channel, while the walls of the diffuser are connected hollow cooled pylons, which are made with concave and convex walls. 2. The double-circuit gas turbine engine according to claim 1, characterized in that the walls of the diffuser and the concave walls of the pylons are made with holes.

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