JPH10184389A - Gas turbine engine - Google Patents

Abstract

PROBLEM TO BE SOLVED: To optimize the temperature condition of inlet guide vanes, and enhance the anti-icing property of a strut by forming a hollow part in the strut arranged upstream of the inlet guide vane, by circulating the high-temperature air from a compressor to the hollow part, and providing jetting ports of the high-temperature air in the side wall part of the strut. SOLUTION: An inlet guide vane 3 is arranged upstream of the moving blade of a gas turbine engine, while a strut 4 having a hollow part 4a is arranged immediately upstream of the guide vane 3. A plurality of jetting ports 4c are formed on the side wall part of the strut 4, and each of the jetting ports 4c is arranged in such a state that the opening rate is increased from the forefront end of the strut 4 toward the center of the turbine engine in the radial direction, and also that each port is inclined toward the downstream. By passing the high-temperature air extracted from a compressor into the hollow part 4a, the surface temperature of the strut 4 is increased to obtain an anti-icing effect, and also by jetting the high-temperature air through jetting ports 4c, the high-temperature air is prevented from being directly jetted on the inlet guide vane 3.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a gas turbine engine, and more particularly to a technique suitable for preventing icing of a gas turbine engine.

[0002]

2. Description of the Related Art FIGS. 2 and 3 show an example of a gas turbine engine. Reference numeral 1 denotes a gas turbine engine, 2 denotes a moving blade, and 3 denotes an inlet guide vane (I).
GV), 4 struts, 5 is a duct for heated air, and 6 is an external pipe.

In such a gas turbine engine 1, high-temperature air of about 400 ° C. extracted from the latter stage of the compressor is guided to a heated air duct 5 by an external pipe 6, and as shown in FIG. By feeding the strut 4 into the hollow portion 4a to warm the strut 4 and ejecting the strut 4 from the ejection port 4b toward the inlet guide vane 3 at a downstream position to heat the inlet guide vane 3, ice adheres to the strut 4 and the like, thereby causing IG.
The V is prevented from moving or peeled off after growing to prevent the ice from being sucked into the compressor.

[0004]

However, in order to reduce the weight of the gas turbine engine 1, a fiber reinforced plastic (Fiber reinforced plastic;
Although the application of FRP) or the like is conceivable, since the temperature of the air passing through the hollow portion 4a of the strut 4 becomes as high as about 400 ° C., when the high-temperature air is ejected backward, the high temperature It is necessary to consider durability.

The present invention has been made in view of the above circumstances, and aims to achieve the following objects. To optimize the temperature condition for the inlet guide vane. Improve the ice protection of struts. To enable the application of fiber reinforced plastic to the inlet guide wing.

[0006]

A gas turbine engine having an inlet guide vane disposed upstream of a rotor blade and a strut disposed upstream of the inlet guide vane, wherein the strut has a hollow portion. The high-temperature air extracted from the compressor is inserted into the hollow portion, and a spout for discharging the high-temperature air from the hollow portion to the side wall portion of the strut is disposed. A plurality of ejection ports are arranged in a state inclined downstream. A technique is selected in which a plurality of ejection ports having the same opening area are arranged in a state where the opening ratio is increased from the tip of the strut toward the center in the radial direction. A technique is employed in which a plurality of ejection ports having different opening areas are arranged, and the opening area near the base of the strut is set large.

[0007]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of a gas turbine engine according to the present invention will be described below with reference to the drawings.

As described above with reference to FIGS. 2 and 3, in the gas turbine engine 1, the inlet guide vanes 3 are disposed upstream of the moving blades 2, and the struts 4 are disposed immediately upstream thereof. However, in one embodiment shown in FIG.
A plurality of spouts 4 c are arranged on the side wall of the strut 4.
The material of the entrance guide vane 3 is, for example, fiber reinforced plastic (FRP).

The plurality of jet ports 4c are, for example, round holes having the same opening area. The plurality of ejection ports 4c
For example, they have the same opening area, but are arranged in a state where the opening ratio is increased from the tip of the strut 4 toward the radial center of the turbine engine 1 and, as shown in FIG. Placed in a state.

During the operation of the gas turbine engine 1, outside air flows into the gas turbine engine 1 as shown by an arrow A in FIG. To prevent the adhesion of ice due to weather conditions or the like, high-temperature and high-pressure air (for example, about 400 ° C.) is extracted from the latter stage of the compressor, guided to the upstream by the external pipe 6, and is heated by the duct 5 for the heated air. As shown by arrow B in FIG. 2, this high-temperature air is ejected to both sides and slightly downstream from the ejection port 4c through the hollow portion 4a of the strut 4 and the inside of the gas turbine engine 1 as shown by an arrow B in FIG. It mixes with the outside air which flowed into.

The strut 4 when hot air is blown out
When the surface temperature is about 100 ° C., an effect of preventing the strut 4 from icing can be obtained. At this time, hot air is
By jetting the gas from the jet port 4 c to the side of the strut 4, the gas can be mixed with the outside air flowing into the gas turbine engine 1, so that the hot air does not directly enter the inlet guide vanes 3.

When high-temperature air is jetted downward from the jet port 4c, it can smoothly join the air flow near the strut 4.

The plurality of jet ports 4c are distributed so that the number of bases of the strut 4 is increased, so that high-temperature air can be appropriately sent to a portion where icing is likely to occur.

The jet ports 4c are formed so as to have different sizes (open areas) from each other.
It is also possible to arrange a large opening area in the vicinity of the base.

[0015]

According to the gas turbine engine of the present invention, the following effects can be obtained. (1) By mixing the high-temperature air jetted from the jet port with the outside air, it is possible to optimize the temperature state with respect to the inlet guide vane. (2) The anti-icing property of the strut can be enhanced by ejecting high-temperature air from the ejection port to the side of the strut. (3) The application of fiber-reinforced plastic to the inlet guide wing can be enabled.

[Brief description of the drawings]

FIG. 1 is a cross-sectional view of a strut illustrating an embodiment of a gas turbine engine according to the present invention.

FIG. 2 is a longitudinal sectional view showing an example of a conventional gas turbine engine.

FIG. 3 is a front view of the gas turbine engine of FIG. 2;

FIG. 4 is a view as viewed in the direction of arrows XX in FIG. 2;

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 ... Gas turbine engine 2 ... Blade 3 ... Inlet guide blade 4 ... Strut 4a ... Hollow part 4b, 4c ... Injection port 5 ... Duct for heated air 6 ... External piping

Claims (5)

[Claims] A gas turbine engine (1) having an inlet guide vane (3) arranged upstream of a rotor blade (2) and a strut (4) arranged upstream of the inlet guide vane. The strut is provided with a hollow portion (4a) through which high-temperature air extracted from the compressor is inserted and through which the high-temperature air is blown out from the hollow portion to the side wall of the strut. A gas turbine engine provided with an injection port (4c). 2. The gas turbine engine according to claim 1, wherein a plurality of the jet ports (4c) are provided. 3. A plurality of outlets (4c) having the same opening area.
3. The gas turbine engine according to claim 1, wherein the gas turbine engine is arranged such that an opening ratio increases from a tip end of the strut (4) toward a radial center. 4. 4. The gas turbine engine according to claim 1, wherein a plurality of jet openings (4c) having different opening areas are arranged, and the opening area near the base of the strut (4) is set large. 5. The jet outlet (4c) is disposed in a state inclined downstream.
A gas turbine engine as described.