JPS587801B2 - High temperature turbine cooling blade - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION The present invention relates to high-temperature turbine cooling blades used for moving blades and stationary blades of high-temperature turbine sections in jet engines and gas turbines.

In general, gas turbine engines can reduce fuel consumption and increase output by increasing the turbine inlet temperature.

However, the heat resistance temperature of metal is limited to around 900℃,
Therefore, when the gas temperature is higher than this, a high temperature turbine with cooling blades is used.

In recent years, for the cooling blades of such high-temperature gas turbines, efforts have been made to improve the cooling effect (cooling the blades with as little air as possible) by skillfully combining cooling by convection of cooling air, impingement cooling, and film cooling. Various things are being considered.

Figures 1 and 2 show an example of a conventional high-temperature turbine cooling blade, in which the turbine cooling blade exposed to high-temperature gas a is cooled by cooling air supplied from a hollow part b. Moreover, the internal structure is generally designed to increase the heat transfer coefficient, increase the heat transfer area, and at the same time control the amount of air blown to the wing surface.

However, in such conventional high temperature turbine cooling blades,
Efforts have not yet been made to increase the heat transfer area on the side of the hollow part b of the inner wing plate C, and therefore the heat transferred from the outer wing plate d to the inner wing plate C via the partition plate e must be sufficiently cooled by convection. There is a drawback that it cannot be done.

In addition, the cavity f is made large in order to stabilize the control of the amount of air blown out to the outer peripheral blade surface of the wing skin d.
The distance g between the inner surface of the wing outer plate d and the outer surface of the wing inner plate C increases, and therefore impingement cooling (air collides with the inner surface of the wing outer plate d) by air blown into the cavity f from the vent h The disadvantage is that the cooling provided by the process is not sufficient.

The present invention was made in order to solve the drawbacks of the above-mentioned conventional system, and a cavity is formed between a wing outer plate having a blowout hole and a wing inner plate having a ventilation hole through a partition plate. A mountain portion is formed around the opening of the ventilation hole into the cavity on the outer surface of the blade inner plate, and a trough portion is formed at a position facing the blowout hole, and further, a fin is provided to protrude from the inner surface of the blade inner plate. The present invention relates to a high-temperature turbine cooling blade characterized by:

Embodiments of the present invention will be described below with reference to the drawings.

3 to 7 show an example of the cooling blade of the present invention applied to a gas turbine stator blade. As shown in FIGS. 3 and 4, the cooling blade mainly consists of the blade outer plate 1 and the blade. It is composed of an inner plate 2 and is integrally fixed to a wing attachment part 3, and the upper wing inner plate 2 forms a hollow part 5 into which cooling air 4 is introduced.

Further, referring to FIGS. 5 to 7, which show the main parts of the present invention in detail, cooling air 4 is blown onto the blade skin 1 from the inner surface to the outer surface along the flow of high-temperature gas 6. A large number of air outlet holes 7 are provided at predetermined intervals for air discharge, and a fin-shaped partition plate 8 is provided on the inner surface of the blade outer plate 1 to separate the air outlet holes 7. A cavity 9 is formed between the wing outer plate 1 and the wing inner plate 2 by the shaped partition plate 8 .

Further, the fin-shaped partition plate 8 is formed so that the portion on the side of the blade outer plate 1 is thick and gradually becomes thinner toward the inside in order to improve heat transfer from the blade outer plate 1.

Furthermore, fins 10 are formed on the inner surface of the inner blade plate 2 so as to protrude into the hollow portion 5 and have a shape that is an extension of the tapered shape of the fin-shaped partition plate 8 .

The air outlet hole 7 is provided in the inner blade plate 2 in communication with the cavity portion 9.
A ventilation hole 11 is provided to send cooling air 4 to the air conditioner.

Further, the ventilation hole 11 is arranged at a shifted position from the blow-off hole 7 so as not to overlap.

Further, a mountain portion 12 is formed on the outer surface of the blade inner plate 2 at a portion where the ventilation hole 11 is provided so as to reduce the distance from the inner surface of the blade outer plate 1. A trough portion 13 is formed at the position.

The above-mentioned blade outer plate 1 and blade inner plate 2 are manufactured separately by precision casting or forging and then diffusion bonded, or integrally formed by integral casting, and the cooling blade and the blade attachment part 3 are also welded or integrally formed. Formed by casting.

Further, the blowout hole 7 and the ventilation hole 11 are formed by casting or an electrochemical method.

According to the turbine cooling blade having the above-described configuration, the blade inner plate 2
The cooling air 4 introduced into the hollow part 5 causes the fins 10 to
are convection cooled, and the convection cooling effect of the blade inner plate 20 on which the fins 10 are provided is significantly improved.

Furthermore, by cooling the blade inner plate 2, the blade outer plate 1 is conductively cooled via the fin-shaped partition plate 8.

Further, the cooling air 4 is introduced into the cavity 9 through the ventilation holes 11, but at this time, the airfoil inner plate 2, which the ventilation holes 11 are open to, is introduced into the cavity 9.
By forming the peak part 12 on the outer surface of the vent hole 1
1 and the inner surface of the blade skin 1 becomes narrower, so that impingement cooling of the blade skin 1 is effectively performed.

The cooling air 4 that has been subjected to impingement cooling advances within the cavity 9 toward the blowout hole 7 .

At this time, since the trough 13 is formed near the blow-off hole 7, the cavity 9 is widened, so that the static pressure is sufficiently recovered and the amount of cooling air 4 blown out from the blow-off hole 7 is sufficiently stabilized. be able to.

The cooling air 4 blown out from the air outlet 7 is
An air film S is formed along the surface of the blade skin 10, and film cooling is performed so that the blade skin 1 is not directly exposed to the high temperature gas 6, thereby blocking heat from the high temperature gas 6 to the blade skin 1. .

Therefore, as mentioned above, cooling by convection, cooling by impingement, and film cooling are effectively combined to significantly improve the cooling effect, and the temperature of turbine blades operating under high-temperature gas conditions can be lowered to the limit of material use. It can be held as below.

However, the fins 10 in the above embodiments may be formed in a direction perpendicular to or inclined to the illustrated arrangement, and the fins 10 themselves may also be modified in various ways, such as having a wave shape.

Furthermore, the shapes of the fin-like partition plate 8, the peaks 12, the valleys 13, etc. can be modified in various ways without departing from the gist of the present invention, and the present invention can be applied as cooling blades for various turbine blades. It is something that can be done.

According to the high temperature turbine cooling blade of the present invention described above, (i)
By providing fins on the inner surface of the blade inner plate, the heat transfer area increases and the convection cooling effect can be improved.

(11) By forming a peak around the opening of the vent on the outer surface of the wing inner plate, the distance between the inner surface of the wing outer plate and the opening can be narrowed, and therefore the inner surface of the wing outer plate Impingement cooling can be performed effectively.

In addition, a valley is formed on the outer surface of the wing inner plate opposite to the position where the air outlet hole is provided in the wing outer plate to maintain a wide cavity space, thereby reducing the static pressure of the cooling air. It is possible to recover and blow out a stable amount of air from the blow-off holes to the outside of the blade.

(m) By effectively performing convection cooling and impingement cooling at the same time, the overall cooling effect including film cooling is significantly improved.

etc., exhibits various excellent effects.

[Brief explanation of the drawing]

Fig. 1 is a cutaway side view showing an example of a conventional high-temperature turbine cooling blade, Fig. 2 is an enlarged view of section A in Fig. 1, and Fig. 3 is an example of the cooling blade of the present invention applied to a gas turbine stationary blade. FIG. 4 is an enlarged view of FIG. 3 viewed from the IV-II direction, FIG. 5 is a partially enlarged explanatory view of FIG. 4, and FIG. 6 is an enlarged view of FIG. An explanatory diagram showing a part removed when viewed from
FIG. 7 is a view taken along arrows 1 and 2 in FIG. 6. 1 is a wing outer plate, 2 is a wing inner plate, 5 is a hollow part, 7 is a blowout hole,
8 is a fin-shaped partition plate, 9 is a cavity, 10 is a fin, 11
12 indicates a vent, 12 indicates a peak, and 13 indicates a trough.

Claims (1)

[Claims] 1 A cavity is formed via a partition plate between a wing outer panel having a blowout hole and a wing inner panel having a ventilation hole, and a cavity is formed around the opening of the vent to the cavity on the outer surface of the wing inner panel. A high-temperature turbine cooling blade characterized in that a peak part and a trough part are formed at a position facing the blowout hole, and further, fins are provided protruding from the inner surface of the blade inner plate.