RU2268379C1 - Ground-based gas-turbine engine - Google Patents

Abstract

FIELD: mechanical engineering.

SUBSTANCE: ground-based gas-turbine engine comprises compressor, collector of fresh air, collector for mixed air, combustion chamber, working turbine, free power turbine, and exhaust scroll. The exhaust scroll is additionally provided with the ejector connected with the fresh air collector through the air duct and with the collector of the mixed air through the air duct for supplying the mixture of air and the exhaust gases. The collector of fresh air is mounted downstream of the compressor. The collector of the mixed air is mounted upstream of the combustion chamber.

EFFECT: enhanced efficiency.

1 dwg

Description

A land-based gas turbine engine belongs to the field of mechanical engineering and can be used to create aircraft-type gas turbine engines designed to drive various machines, for example, current generators or gas compressor stations of main pipelines for transporting natural gas.

Known gas turbine engines (GTE), for example, the engine NK-38ST OJSC "SNTK im. ND Kuznetsova ”, engine PS-90GP-1 of Perm Engine Company OJSC used as a drive for gas compressors of gas pumping units, compressor stations, current generators in power plants containing a gas generator and a free (or power) turbine that converts gas energy flow after the working turbine of the gas generator into the energy of the rotational motion of its rotor and transmitting torque to the consumer ("Analysis of the main layout and technical solutions adopted by various GPU manufacturers when they were developed tke ”album of OJSC“ Sumy NPO named after MV Frunze ”, 2001, p. 77, 80, see appendix).

The closest in technical essence is the layout of the NK-16-18ST series 2 engine, developed by Aviamotor OJSC and Kazan Motor-Building Production Association OJSC (manufacturer), adopted as a prototype that contains a gas generator and a free (or power) turbine that converts the energy of the gas stream after the working turbine of the gas generator into the energy of the rotational motion of its rotor (Promotional brochure of OJSC Kazan Motor-Building Production Association, NK-16- driving gas turbine engine 18ST series 2, see copy in the appendix).

A characteristic feature of known engines, including those adopted as a prototype, is that the amount of air supplied by the compressor of the gas generator (cycle air) to the entrance to its combustion chamber is significantly, 4 or more times higher than that necessary to ensure fuel combustion. This is dictated by temperature limitations from the applied structural materials of parts and assemblies operating at high temperatures.

Known engines provide a relatively low coefficient of performance (COP), which is the engine NK-16 ST, for example, only 29%.

The objective of the proposed technical solution is a significant increase in efficiency in relation to the well-known engines, including engines of the NK-16-18 ST series.

The problem is solved due to the fact that the land-based gas turbine engine contains a compressor, a clean air collector, a mixed air collector, a combustion chamber, a working turbine, a free power turbine, an exhaust snail, while the exhaust snail is additionally equipped with an ejector connected to the clean air collector by an air duct installed behind the compressor and the duct for supplying a mixture of air with exhaust gases with a mixed air manifold located in front of the combustion chamber.

The drawing schematically shows a land-based gas turbine engine, which contains a compressor 1, a clean air manifold 2, a mixed air manifold 3, a combustion chamber 4, a working turbine 5, a free power turbine 6, an exhaust snail 7 with an ejector, a clean air intake duct 8, an air duct supplying a mixture of air and exhaust gases 9.

Behind the compressor 1, a clean air collector 2 is installed, connected by a clean air intake duct 8 with an exhaust snail ejector 7 installed at the output of a free power turbine 6. Beyond the clean air collector 2, there is a mixed air collector 3 connected by an air duct 9 to supply the mixture of air and exhaust gases ejector exhaust snails 7, the combustion chamber 4 and the working turbine 5.

A gas turbine engine of land use works as follows. Atmospheric air taken by compressor 1 enters the clean air collector 2 installed at its outlet and through the clean air intake duct 8 as an “active” component into the ejector installed in the exhaust coil 7 at the outlet of the free power turbine 6. With this arrangement, atmospheres take part of the required mass amount of cyclic air. The second, missing part of the air is obtained using an ejector placed in the exhaust snail 7 from the exhaust gas stream. The air is compressed in the compressor 1 to a pressure that exceeds the required calculated for the total amount of air involved in the cycle. "Active" air, passing through an exhaust coil 7 with an ejector, captures part of the exhaust gases and is mixed with them through the mixed air supply duct 9 through a compressed air manifold 3 to the entrance to the combustion chamber 4. A portion of the cyclic air is recycled. The next part of the cycle occurs, as in the engine, taken as a prototype.

The essence of the proposed technical solution consists in the fact that as the cyclic air in the thermodynamic cycle of the engine, not only atmospheric air taken and pumped by the gas generator compressor directly from the atmosphere is used, but also air mixed with combustion products taken from the exhaust system at the outlet of free power engine turbines containing a sufficient amount of oxygen and having a temperature approximately the same as the air leaving the compressor.

The selection of clean air immediately after the compressor, mixing it with exhaust gases using an ejector and supplying an already heated mixture to the combustion chamber reduces the amount of fuel burned in the combustion chamber, i.e. consumed by the engine, which determines a higher efficiency of the engine with recirculation of cyclic air by compared with the known.

Claims (1)

A land-based gas turbine engine comprising a compressor, a clean air manifold, a mixed air manifold, a combustion chamber, a working turbine, a free power turbine, an exhaust snail, characterized in that the exhaust snail is additionally equipped with an ejector connected to the fresh air manifold by the duct mounted behind the compressor, and an air duct for supplying a mixture of air with exhaust gases with a mixed air manifold located in front of the combustion chamber.