EP1266128B1 - Reinforcement and cooling structure of a turbine blade - Google Patents

Abstract

The invention relates to a blade (13; 14) for a turbine (10) which has at least one channel (22) that can be impinged with a coolant fluid. Several turbulators (23) which improve the heat exchange between the wall (19; 20) and the coolant fluid are provided on at least one wall (19; 20) of the channel (22). In addition, the turbulators (23) reinforce the wall (19; 20) and converge. As a result of said reinforcement, the thickness (d) of the wall (19; 20) in the area between the turbulators (23) can be reduced.

Description

The present invention relates to a blade, in particular a turbine blade with at least one channel, the bounded by walls and acted upon by a cooling fluid is, wherein on at least one wall several turbulators for Improvement of the heat exchange between the wall and the Cooling fluid are provided.

Such a turbine blade is for example from the EP 0 758 932 B1. This known turbine blade is hollow and has four channels. The channels will be each of the two outer walls of the turbine blade and Partitions limited and for cooling with a cooling fluid flows through. To improve the heat exchange between the outer walls and the cooling fluid are the outer walls with Provided turbulators.

In the known turbine blade, the turbulators serve only to improve the heat exchange. The in operation occurring loads on the turbine blade almost exclusively absorbed by the exterior walls, the must therefore be made relatively thick. For enlargements the load must continue the wall thickness of the outer walls increase. However, this increase in wall thickness decreases the cooling efficiency and thus the overall efficiency.

Object of the present invention is therefore a blade provide a higher load capacity without magnification the wall thickness or a reduction in the Wall thickness allows for the same load capacity.

According to the invention is to solve this problem in a Shovel of the type mentioned provided that the turbulators serve to stiffen the wall and into each other pass.

According to the invention for the first time the turbulators for stiffening used on the wall and merge into each other. hereby will be a substantial increase in stiffness without additional Material and without increasing the wall thickness reached. At the same time, a good heat exchange between the walls and the cooling fluid. This results in a high cooling efficiency and high overall efficiency.

The stiffening of the wall is not just in the area of one single turbulator. It is rather by the Connecting the turbulators together a large area Stiffening provided.

Advantageous embodiments and developments of the invention are apparent from the dependent claims.

Advantageously, the turbulators are straight. The Use of straight turbulators allows high rigidity with simple production.

In an advantageous first embodiment, all include Turbulators with a longitudinal axis of the blade the same angle one. This results in a symmetrical arrangement of the turbulators, the loads from all directions evenly can record.

According to an advantageous development close the turbulators a right angle. Alternatively, a can Sharp or obtuse angle can be selected.

According to an advantageous second embodiment includes a first group of turbulators with a longitudinal axis of the blade a first angle and a second group of turbulators with the longitudinal axis of the blade a second angle.

The two groups of turbulators thus have different Inclinations towards the longitudinal axis of the blade. The rigidity of the blade therefore depends on the direction of attack the burden. Due to the different inclination Thus, a specific adaptation of the stiffness in different Directions are achieved.

Advantageously, the turbulators are arranged such that they beside and overlying recesses in the form of Forming polygons, in particular squares, diamonds or hexagons. The inside of the wall is made with a honeycomb structure Mistake. The individual polygons or honeycombs form each a closed, highly loadable cross-section and support off each other. It can be a significant increase to achieve rigidity.

In an advantageous embodiment, the wall thickness of the wall reduced at least in the area between the turbulators. This reduction in wall thickness is thereby made possible that the turbulators effect a stiffening of the wall. By reducing the wall thickness becomes the cooling efficiency increased again. The turbulators can be advantageous here used in casting the blade as metal feed channels become. The honeycomb structure is therefore easy to produce.

According to an advantageous embodiment, the blade several with different arrangements of turbulators provided sections. Through these different arrangements settles in the individual sections of the blade influence the rigidity in a targeted manner. It results in an optimal Adapting to the particular section of the Shovel present loads.

In an advantageous first development, the sections are mutually spaced. This will be a simple change between different arrangements of turbulators allows.

According to a second advantageous development, the sections go into each other. It results in a continuous Increasing the rigidity of the blade.

The blade according to the invention can be used as a vane or as Blade of a rotary machine can be formed.

FIG 1

einen Längsschnitt durch eine Rotationsmaschine;

FIG 2

eine perspektivische, aufgebrochene Darstellung einer Schaufel;

FIG 3

eine vergrößerte Darstellung der Einzelheit X aus Figur 2;

FIG 4

eine Draufsicht auf die Innenseite einer Außenwand der Schaufel in erster Ausgestaltung;

FIG 5

eine Ansicht ähnlich Figur 4 in zweiter Ausgestaltung;

FIG 6

eine Ansicht ähnlich Figur 4 in dritter Ausgestaltung;

FIG 7

eine schematische Darstellung einer Laufschaufel; und

FIG 8

eine schematische Darstellung einer Leitschaufel.

The invention will be described in more detail below with reference to exemplary embodiments, which are shown schematically in the drawing. For identical or functionally identical components, the same reference numerals are used throughout. Showing:

FIG. 1

a longitudinal section through a rotary machine;

FIG. 2

a perspective, broken-away view of a blade;

FIG. 3

an enlarged view of the detail X of Figure 2;

FIG. 4

a plan view of the inside of an outer wall of the blade in the first embodiment;

FIG. 5

a view similar to Figure 4 in the second embodiment;

FIG. 6

a view similar to Figure 4 in the third embodiment;

FIG. 7

a schematic representation of a blade; and

FIG. 8

a schematic representation of a vane.

FIG. 1 shows a longitudinal section through a rotary machine in the form of a turbine 10 with a housing 11 and a rotor 12. The housing 11 is provided with guide vanes 13 and the rotor 12 provided with blades 14. In operation, the turbine 10 flows through a fluid according to arrow 15, the on the guide vanes 13 and blades 14 flows along and the rotor 12 is rotated about an axis 16.

The temperature of the fluid is in many applications, in particular in the area of the first blade row (in FIG. 1) shown on the left), relatively high. It is therefore a cooling the guide vanes 13 and blades 14 are provided. The Flow of the cooling fluid is schematically indicated by the arrows 17, 18th indicated. In particular, air can be used as the cooling fluid become.

Figure 2 shows schematically a broken-away view of a Guide vane 13. The vane 13 has curved outer walls 19, 20 on. The lying between the outer walls 19, 20 Interior is divided into two partitions 21 in total divided into three channels 22. In operation, the channels 22 subjected to a cooling fluid.

To improve the heat exchange between the outer walls 19, 20 and the cooling fluid are the outer walls 19,20 with several turbulators 23 provided. For the sake of drawing Representation, the turbulators 23 in Figure 2 are strong shown in simplified form. However, it is clear that the Turbulators 23 merge into one another and a honeycomb structure form. This honeycomb structure causes a stiffening of the outer walls 19, 20.

Figure 3 shows an enlarged view of the detail X. from Figure 2. The turbulators 23 are straight and formed go into each other. In the illustrated embodiment is limited by four turbulators each a recess 24. The wall thickness d of the outer wall 19 decreases starting from the turbulators 23 kontiunierlich to Center of the recess 24. This reduction in the wall thickness d is thereby made possible that the turbulators 23 to each other support and thereby the rigidity of the vane 13 increase significantly. The turbulators 23 serve simultaneously as impact protection.

Due to the reduced wall thickness d results in a higher Cooling efficiency. It therefore requires less cooling fluid, so that a higher overall efficiency of the turbine 10 can be achieved leaves.

The turbulators 23 are approximately triangular in cross section designed and rejuvenated starting from the outer wall 19. You can therefore when pouring the vane 13 than Serve metal feed channels. The guide vane according to the invention 13 is thus easy to manufacture.

FIGS. 4 to 6 show a schematic plan view the inside of the outer wall 19 in three different Configurations. In the embodiment of FIG 4 close All turbulators 23a, 23b the same angle α, β with a longitudinal axis 25 of the vane 13 a. The turbulators 23a, 23b close together a right angle 26 a. The recesses 24 delimited by the turbulators 23a, 23b thus form squares.

A turbulator 23a, 23b extends between each two Touch points 31. In the area of touch points 31 go the Turbulators 23a, 23b into each other. By use straight turbulators 23a, 23b, the production is simplified. Next results in a high rigidity.

In the embodiment according to FIG. 5, a first one closes Group of turbulators 23 a a first angle α with the Longitudinal axis 25, while a second group of turbulators 23b includes a second angle β with the longitudinal axis 25. The angle 26 between the turbulators is in this Design greater than 90 °. It follows accordingly a recess 24 in the form of a rhombus. By the different Inclination of the turbulators 23a, 23b with respect to Longitudinal axis results in a different stiffness of the Guide vane 13 depending on the loading direction.

It will thus be a good adaptation to different boundary conditions reached.

In the embodiment according to FIG. 6, six turbulators each form 23 a recess 24 in the form of a hexagon. It This results in a honeycomb structure that reduces the rigidity of the vane 13 substantially increased.

Of course, other suitable arrangements may be made of turbulators 23 are used. Be beneficial the turbulators 23 arranged such that in the figures 4 to 6 shown recesses 24 arise. These recesses 24 have a closed plan view Cross-section and therefore a high rigidity. alternative The turbulators 23 may also be arranged in the form of a V or X. become.

Of course, the turbulators 23 also at a Blade 14 may be provided. In Figure 7 is schematic such a blade 14 is shown, the more with different arrangements of turbulators 23 provided Sections 28, 29, 30 has. The arrangement of the section 28 corresponds to the representation according to FIG. 4, while FIG the sections 29, 30 formed according to Figures 5 and 6 are. The individual sections 28, 29, 30 are mutually spaced. In the area between sections 28, 29, 30 may cross-sectional or shape changes of the blade 14 be made with low production costs. To achieve the required rigidity is the Wall thickness d of the outer walls 19, 20 in these transition areas increased accordingly. The use of different Arrangements of turbulators 23 allows a targeted influence the stiffness of the blade 14 in the individual Sections 28, 29, 30. This results in an optimal Adaptation to different boundary conditions along the Longitudinal axis 25.

The sections 28, 29, 30 can also merge into one another, as shown schematically on the basis of a vane 13 in Figure 8. The turbulators 23 of the individual sections 28, 29, 30 go here in touch points not shown into each other. This results in a continuous Stiffening of the vane 13 along its longitudinal axis 25th

The present invention enables an increase in rigidity through a targeted arrangement of improvement heat exchangers provided turbulators. At the same Load can reduce the wall thickness d of the outer walls 19, 20 become. By this reduction in wall thickness is the Cooling efficiency increased, so that an overall higher Overall efficiency of the turbine 10 results.

Claims (11)

1. Blade/vane, in particular a turbine blade/vane (13; 14), having at least one duct (22), which is bounded by walls (19, 20, 21) and to which a cooling fluid can be admitted, a plurality of turbulators (23) being provided on at least one wall (19; 20) to improve the heat exchange between the wall (19; 20) and the cooling fluid, characterized in that the turbulators (23) merge into one another and are used to reinforce the wall (19; 20).
2. Blade/vane according to Claim 1, characterized in that the turbulators (23) have a straight configuration.
3. Blade/vane according to Claim 2, characterized in that all the turbulators (23a, 23b) include the same angle (α, β) with a longitudinal centre line (25) of the blade/vane (13; 14).
4. Blade/vane according to Claim 2 or 3, characterized in that the turbulators (23a, 23b) include a right angle (26).
5. Blade/vane according to Claim 2, characterized in that a first group of turbulators (23a) includes a first angle (α) with a longitudinal centre line (25) of the blade/vane (13; 14) and a second group of turbulators (23b) includes a second angle (β) with the longitudinal centre line (25) of the blade/vane (13; 14).
6. Blade/vane according to one of Claims 2 to 5, characterized in that the turbulators (23) are arranged in such a way that they form recesses located adjacent to one another and above one another in the form of polygons, in particular squares, rhombuses or hexagons.
7. Blade/vane according to one of Claims 1 to 6, characterized in that the wall thickness (d) of the wall (19; 20) is reduced, at least in the region between the turbulators (23).
8. Blade/vane according to one of Claims 1 to 7, characterized in that the blade/vane (13; 14) has a plurality of sections (28, 29, 30) provided with different arrangements of turbulators (23).
9. Blade/vane according to Claim 8, characterized in that the sections (28, 29, 30) are at a distance from one another.
10. Blade/vane according to Claim 8, characterized in that the sections (28, 29, 30) merge into one another.
11. Blade/vane according to one of Claims 1 to 10, characterized in that the blade is configured as a guide vane (13) or as a rotor blade (14) of a turbomachine (10).

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