RU182721U1 - GAS-TURBINE ENGINE AIR COOLING SYSTEM - Google Patents

Abstract

The gas turbine engine air cooling system is used to lower the temperature of the gas turbine drive engine located in the compartment. The air cooling system of the gas turbine engine (1) located in the compartment (2) contains an annular channel (3) formed by the casing (4) and the housing (5) of the engine (1). The annular channel (3) is in communication with the turbine diffuser (6), and in the compressor zone (7) through the ventilation windows (8) and flexible pipes (9) with the atmosphere. Adjustable shutters (10) are installed in the ventilation windows (8). The supply of cooling air through the nozzles (9) directly to the housing (5) of the engine (1) provides effective uniform cooling of the heated surfaces of the engine (1) and eliminates the cooling of the entire compartment (2).

Description

The utility model relates to gas turbine engineering and can be used in units using a gas turbine engine (GTE) as a drive, which requires constant guaranteed cooling.

At the present stage of development of mechanical engineering, gas turbine power plants and gas pumping units in block-container design, consisting of separate transportable blocks, are widely used. When placing a gas turbine engine in a compartment, certain requirements are imposed on its cooling.

A known system for cooling a gas turbine engine located in the compartment, forming an annular chamber with the engine body, a fan block, a gas manifold connected to it with holes facing the cooled surface of the engine, as well as a ring receiver of heated air placed in the annular chamber behind the cooled surface and communicating with the external environment by the flue (patent No. 2460893, IPC F02C 7/18, publ. 09/10/2012).

The disadvantage of this device is that it does not provide uniform cooling of the engine, since the flow of cooling air in such a circuit is uneven around the circumference. In order to ensure an acceptable level of air temperature under the casing, to eliminate stagnant zones, high-flow purging is required. Moreover, the gas-dynamic resistance of such a device is quite large. As a result, powerful fans are required, which leads to an increase in the cost of manufacturing and operating such an installation.

It is also known a ventilation device of the gas turbine engine compartment of a gas pumping unit, comprising a compartment with a centrifugal exhaust fan, gas turbine engine with internal and external shells forming a channel with hot air, technological windows according to the diameter of the outer shell and a high pressure compressor. To reduce the temperature in the compartment, the gas turbine engine is additionally equipped with an air duct for venting hot air directly into the atmosphere through one of its open technological hatches, using active air pumped into the air duct through a separate pipe from a high-pressure compressor as an ejector (RF patent No. 2226017, dated 10.02.2005, F02C 7/12).

The disadvantage of this device is that the air cooling the hottest surfaces of the gas turbine engine (housing) is ejected from the gas turbine engine compartment through the windows in the casing. This leads to the fact that in the cold period the compartment cools down, since all ventilation air (high flow rate) is sucked from the atmosphere into the turbine engine compartment, and to ensure a positive temperature inside the compartment, it is required to expend electric energy for heating by electric heaters.

In addition, high-pressure air (“expensive”) taken from the flow part of the gas turbine compressor is used to eject ventilation air, which leads to a decrease in gas-turbine engine characteristics.

The technical result, which is directed to a utility model, is to increase the cooling efficiency of engine surfaces and to prevent cooling of the turbine engine compartment.

The technical result is achieved by the fact that the air cooling system of a gas turbine engine located in the compartment and equipped with a compressor and turbine diffuser, comprising a casing with ventilation windows, forming an annular channel with the engine body.

New in the utility model is that the cooling system is equipped with flexible pipes communicating the annular channel through the ventilation windows with the atmosphere, while the ventilation windows are made in the compressor zone, and the annular channel is in communication with the turbine diffuser.

The ventilation windows have adjustable dampers.

In FIG. 1 and FIG. 2 shows a diagram of the proposed air cooling system of a gas turbine engine.

The air cooling system of the gas turbine engine 1, located in compartment 2, contains an annular channel 3 formed by a casing 4 and a housing 5 of the engine 1. The annular channel 3 is in communication with the turbine diffuser 6, and in the compressor zone 7 through the ventilation windows 8 and flexible tubes 9 with the atmosphere . In the ventilation windows 8, adjustable shutters 10 are installed. From the input device side of the engine 1, the annular channel 5 is blocked by the wall 11.

Arrows indicate the direction of air flow.

The air cooling system of a gas turbine engine operates as follows:

During installation operation, due to the ejection in the turbine diffuser 6, cold air is sucked in from the atmosphere through the nozzles 9 and the windows 8 into the annular channel 3. The air flow passing through the annular channel 3 intensively cools the most heated surfaces of the housing 5 of the engine 1 and, mixing in the turbine a diffuser 6 with a high-energy gas stream exiting the engine 1 is discharged through the exhaust system 12 into the atmosphere.

The remaining excess heat from the gas turbine engine 1 in compartment 2 is removed through the exhaust duct 13 of the ventilation system of compartment 2 of the turbine engine 1.

In the cold season, the purge of the annular channel 3 is reduced by opening and closing the shutters 10 in the ventilation windows 8.

The supply of cooling air through the nozzles directly to the engine housing provides effective uniform cooling of the heated surfaces of the engine and eliminates the cooling of the entire compartment.

Claims (2)

1. The air cooling system of a gas turbine engine located in the compartment and equipped with a compressor and turbine diffuser, comprising a casing with ventilation windows, forming an annular channel with the engine housing, characterized in that the cooling system is equipped with flexible pipes communicating the annular channel through the ventilation windows with the atmosphere, while ventilation windows are made in the area of the engine compressor, and the annular channel is in communication with the turbine diffuser. 2. The air cooling system of a gas turbine engine according to claim 1, characterized in that the adjustable windows are installed in the ventilation windows.

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