JPH11294107A - Turbine blade thermal fatigue testing device - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a device to protect a heating part of a frame body from high temperature gas at a relatively low cost. SOLUTION: In a turbine blade thermal fatigue testing device provided with a frame body to fix a line of turbine blades at an upper and a lower parts, a hot air discharge port 2 and an air discharge port provided in the frame body in parallel in a perpendicular direction to a gas inflow direction on the gas inflow side to turbine blades 4, and a reciprocation device to drive the frame body to move the turbine blade line to be alternately positioned to the hot air discharge port 2 and the air discharge port, water cooling devices 15 are provided on an upper and lower members 5, 6 on the gas inflow side of the frame body.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an apparatus for performing a thermal fatigue test on a turbine blade by alternately blowing hot air and air onto the turbine blade.

[0002]

2. Description of the Related Art As a thermal fatigue test of a high-pressure turbine blade, a test is performed in which high-temperature gas and air are alternately blown onto the turbine blade to check durability. In this test, a thermal fatigue test of a turbine blade is performed by fixing the outlet of the high-temperature gas and the air and moving the turbine cascade alternately between the two outlets.

FIG. 4 shows an example of such a turbine blade thermal fatigue test apparatus. FIG. 5 shows the gas inflow side of the frame 1 that supports the upper and lower cascades of the high-pressure turbine blades 4. Frame 1
A hot air outlet 2 and an air outlet 3 are arranged side by side on the front surface. The frame 1 is configured such that the turbine blade cascade is alternately moved to the positions of the two discharge ports 2 and 3 by a device (not shown). This causes thermal fatigue in the turbine blade. The fuel premixed with air in the preheating combustor is burned in the main combustion chamber to become a high-temperature gas of 1400 to 1600 ° C.
It is discharged from. Air is discharged from the air discharge port 3 at room temperature. The high-temperature gas and air that have passed through the turbine cascade are sucked into the exhaust duct by the suction air and enter the exhaust duct. The control device controls the entire device, such as the reciprocating motion of the frame 1, the fuel flow rate, the amount of combustion air, the amount of air to the air discharge port 3, the amount of suction air, and the like.

FIG. 6 is a cross-sectional view of the frame 1. The frame 1 includes an upper member 5 and a lower member 6. The upper member 5 has a front vertical member 5b and a rear vertical member 5c attached to the lower surface of a horizontal member 5a like teeth of a clog. Wing upper part 7 is rear vertical member 5
c and the front vertical member 5b are in surface contact, and are fixed to the rear vertical member 5c by screws 9. The lower wing 8 and the lower member 6
Has a similar structure.

The upper member 5 and the upper wing 7 constitute an upper space 10a, and the lower member 6 and the lower wing 8 constitute a lower space 10b.
The spaces 10 a and 10 b communicate with the space inside the turbine blade 4 by a flow path (flow path) penetrating the blade upper part 7 and the blade lower part 8. Blade cooling air pipe 11 is provided in both spaces 10a and 10b.
The cooling air is sent to the turbine blade 4 via the two spaces 10a and 10b, and air is blown out from a large number of micro holes provided on the blade surface to perform seepage cooling. Also,
A water jacket 12 is provided on the upper surface of the upper member 5 to cool the upper member 5.

[0006]

FIG. 7 shows a state in which high-temperature gas is blown from the hot air discharge port 2 to the turbine cascade. Since the frame 1 reciprocates, a gap (about 2 mm) is provided between the hot air outlet 2 and the upper member 5 and the lower member 6 as shown in FIG. High-temperature gas leaks above and below the gap and heats the upper and lower members 5 and 6. Therefore, although the water jacket 12 is provided, the cooling effect is small for the following reasons. Since the water jacket is made of stainless steel from the viewpoint of heat resistance, heat transfer is poor and the cooling effect is small. Although the front surface of the upper member is heated, it is difficult to attach the water jacket to the heating position, and the cooling effect is small. A water jacket cannot be attached to the lower member because it is fixed to the drive mechanism of the cascade. For this reason, cooling is performed by air from the surroundings, but the cooling effect is insufficient.

On the other hand, since the high-temperature gas has a high temperature of 1400 to 1600 ° C., cooling thereof is not sufficient.
The lower member 6 was oxidized, burned out, or thermally deformed. Further, when thermally deformed, as shown in FIG. 6, a gap is generated between the contact surface between the front vertical member 5b and the front surface 7a of the upper blade fixing member and the contact surface between the front vertical member 6b and the front surface 8a of the lower blade fixing member. Insufficient cooling air entered, causing wings to burn. As a result, before completing the thermal fatigue test of the turbine cascade, the frame 1 and the turbine blades were burned out and deformed, and a sufficient thermal fatigue test could not be performed. The heating portion of the frame 1 may be made of a platinum material or a ceramic material that can withstand high-temperature gas, but it is considerably expensive.

The present invention has been made to solve such a problem. That is, an object of the present invention is to provide a turbine blade thermal fatigue test device that is relatively inexpensive, can suppress deformation and burning of the frame and the turbine blade, and can perform a sufficient thermal fatigue test. I do.

[0009]

In order to achieve the above object, according to the first aspect of the present invention, there is provided a frame for vertically fixing a turbine cascade, and a gas inflow direction on a gas inflow side of the frame to a turbine blade. And a reciprocating device that drives the frame so that the turbine blade cascade alternately moves to the positions of the hot air discharge ports and the air discharge ports. , A turbine blade thermal fatigue test apparatus, wherein a water cooling device is provided on the gas inflow side of the frame.

[0010] By providing a water cooling device on the member on the gas inflow side of the frame, the member directly exposed to the high-temperature gas is cooled, so that burnout and thermal deformation can be prevented.

In the invention of claim 2, a plurality of water-cooled copper pipes are provided as the water-cooling device on the gas inlet side front surface and the adjacent lower surface of the frame.

By arranging a copper pipe having a high thermal conductivity on the upper and lower members on the gas inflow side of the frame and passing cooling water, these members can be effectively cooled. In addition, the method of disposing the copper pipe becomes an inexpensive cooling device.

[0013]

Preferred embodiments of the present invention will be described below with reference to the drawings. FIG. 1 is a cross-sectional view of a frame 1 of a turbine blade thermal fatigue test apparatus according to the present invention, and FIG.
FIG. 2 is a perspective view showing a relationship between a frame 1 and a hot air discharge port 2.
FIG. 1 corresponds to FIG. 6 described above, and the same members are denoted by the same reference numerals. 6, the water jacket 12 is eliminated in the present embodiment, and a plurality of copper tubes 15 are arranged on the front surface and the adjacent lower surface of the upper member 5 and the lower member 6 on the hot air discharge port 2 side, not shown. The cooling water is supplied from the cooling water supply device. The other points are the same as those of the apparatus shown in FIG. The copper tube 15 has both ends turned behind the apparatus, and is connected to a vinyl tube at a position not affected by heat, so that the frame 1 can reciprocate in the horizontal arrow direction. The copper tube 15 shields the frame 1 from hot air and cools the upper member 5 and the lower member 6, thereby preventing the members 5 and 6 from burning and reducing thermal deformation. Leakage of air from the space 10b is prevented, and sufficient cooling air is supplied into the turbine blades 4. The heating range by the hot air is limited to the upper member 5 and the lower member 6.
Is limited to the front surface of the frame 1 and heat transfer is small. Therefore, only this portion needs to be cooled, and the entire frame 1 need not be cooled.

FIG. 3 shows another embodiment. In this embodiment, a water jacket 16 made of copper is used instead of the copper tube 15 shown in FIG.
Are provided on the front surface and the adjacent lower surface of the upper member 5 and the lower member 6. Copper pipes are connected to both ends of each water jacket 16 and are further connected to vinyl pipes at positions where there is no thermal effect. With this structure, the supply and discharge of the cooling water are performed, and the frame 1 can reciprocate as shown by the horizontal arrows in FIG. Others are the same as FIG. The water jacket 16 is functionally similar to FIG.
In the same manner as the copper tube 15, the upper member 5 and the lower member 6 prevent the front surface from burning and reduce thermal deformation, prevent air from leaking from the upper space 10 a and the lower space 10 b, and provide cooling air inside the turbine blade 4. Is supplied.

[0015]

As described above, according to the present invention, by providing a copper pipe or a water jacket made of copper on the member on the high-temperature gas inflow side of the frame, it is possible to prevent the burning and thermal deformation of these members and to improve the turbine blade. Leakage of cooling air can be prevented,
A sufficient thermal fatigue test can be performed. In addition, an inexpensive apparatus can be obtained by using a copper tube and a copper water jacket.

[Brief description of the drawings]

FIG. 1 is a cross-sectional view of a frame according to an embodiment of the present invention.

FIG. 2 is a perspective view of a frame and a hot air discharge port.

FIG. 3 is a cross-sectional view of a frame according to another embodiment of the present invention.

FIG. 4 is a configuration diagram of a turbine blade thermal fatigue test device.

FIG. 5 is a front view of the frame.

FIG. 6 is a cross-sectional view of a conventional frame.

FIG. 7 is a perspective view of a conventional frame and a hot air outlet.

[Explanation of symbols]

 DESCRIPTION OF SYMBOLS 1 Frame 2 Hot air discharge port 3 Air discharge port 4 Turbine blade 5 Upper member 5a Horizontal member 5b Front vertical member 5c Rear vertical member 6 Lower member 6a Horizontal member 6b Front vertical member 6c Rear vertical member 7 Upper blade fixing member 7a Upper wing fixing material front surface 8 Lower wing fixing material front 8a Lower wing fixing material front surface 9 Screw 10a Upper space 10b Lower space 11 Blade cooling air pipe 12 Water jacket 15 Copper pipe 16 Water jacket

Claims (2)

[Claims] 1. A frame body for vertically fixing a turbine cascade,
A hot air outlet and an air outlet provided side by side with the gas inflow direction to the turbine blades of the frame in a direction perpendicular to the gas inflow direction, and the turbine cascade is positioned at the hot air outlet and the air outlet. A turbine blade thermal fatigue test device comprising: a reciprocating device for driving the frame so as to move alternately; and a water cooling device provided on a gas inlet side of the frame. apparatus. 2. A turbine blade thermal fatigue test apparatus according to claim 1, wherein a plurality of water-cooled copper pipes are provided on said gas inlet side front surface and adjacent lower surface of said frame body as said water cooling device.