The present disclosure relates to the field of gas turbine technology, and relates to a cooled blade for a gas turbine.
The efficiency of gas turbines can depend on the temperature of hot gas that expands in turbine when performing work. In order to be able to raise the efficiency, the components (stator blades, rotor blades, heat accumulating segments, etc), should not only be produced from heat resistant materials but should also be cooled as effectively as possible during operation. Known methods for blade cooling can be used alternatively or together. One method is to pass a cooling medium, for example, compressed cooling air, from the gas turbine compressor, through an interior of the blades in cooling channels, and to allow it to emerge into a hot gas channel through cooling holes arranged in a distributed manner. The cooling channels can pass through the interior of the blade more than once in a serpentine shape. See, for example, WO A1 2005/068783). The heat transfer between the cooling medium and walls of the blade can be improved by using suitable elements (turbulators) to produce additional turbulence in the cooling medium flow, or by using impingement cooling. In another method, the cooling medium can emerge from the interior of the blade such that a film of cooling medium is formed on the blade surface, and protects the blade (film cooling).
It is desirable to cool the blade tip. The blade tip is furthest away from the blade root, through which the cooling air is supplied. Attention should therefore be paid to its cooling. Furthermore, cooling that is as uniform as possible should be achieved in all operating states, and the consumption of cooling medium should be restricted to what is appropriate, in order to avoid disadvantageously influencing the efficiency of the machine.
DE A1 199 44 923 discloses a comparatively complex solution for cooling the blade tip.
A blade for a gas turbine is disclosed, including an airfoil section extending in a radial direction of the turbine or in a longitudinal direction of the blade between a platform and a blade tip, the blade tip being provided with a cap, the airfoil section being bounded transversely with respect to the longitudinal direction by a leading edge and a trailing edge and having a pressure face and a suction face; cooling channels extending substantially in a radial direction between the platform and the blade tip in an interior of the airfoil section, through which cooling channels a cooling medium flows, first cooling holes for convection cooling provided on the pressure face of the blade; second cooling holes for film cooling provided on the suction face of the blade, the first and second cooling holes being arranged in an area of the blade tip and operatively connected to the cooling channels and distributed over the blade width, the cooling medium being passed to an exterior of the area of the cap and/or through the cap of the blade.
The disclosure will be explained in more detail in the following text with reference to exemplary embodiments and in conjunction with the drawings. The drawings show only those elements which are essential for immediate understanding exemplary embodiments of the disclosure. The same elements are provided with the same reference symbols in the various figures, in which:
a shows an arrangement of cooling holes in a blade tip according to an exemplary embodiment of the disclosure;
b shows in detail some of the film cooling holes at the suction side of the blade according to
a shows part of a longitudinal section through the blade of
b shows part of a longitudinal section through the blade of
c shows an inclination of the film cooling holes at the suction side of the blade according to
a, 4b show different longitudinal sections of the first film cooling holes outside a trailing edge at the pressure side of the blade in
c shows a boundary of an exit of the first film cooling holes according to
a, 5c show different longitudinal sections of the first film cooling holes at the trailing edge at the pressure side of the blade in
b shows a boundary of the exit of the first film cooling holes according to
The disclosure provides a cooled blade for a gas turbine which, for example, provides cooling in the area of the blade tip.
In an exemplary embodiment according to the disclosure, first cooling holes for convection cooling are provided on a pressure face of the blade, and second cooling holes for film cooling are provided on a suction face of the blade, through a cap of the blade, in a blade tip from cooling channels, and distributed over a blade width. The combination of convection cooling on the pressure face and film cooling on the suction face of the blade tip can result in particularly effective and stable cooling without this having any disadvantageous influence on the efficiency.
According to an exemplary embodiment of the disclosure, the first and second cooling holes include at least sections in the form of cylindrical bores with a predetermined first diameter.
The first cooling holes can be in the form of long cylindrical bores which run obliquely upwards and include a first angle of between, for example, 25° and 35° (for example, substantially 30°±10%), with an outer surface of the blade.
According to an exemplary embodiment of the disclosure, the first cooling holes open into an environment of the blade with a fan-shaped section of the bore.
According to an exemplary embodiment of the disclosure, those of the first cooling holes arranged outside the trailing edge of the blade open into the environment of the blade with a 3D symmetric fan-shaped section of the bore, whereby the 3D symmetric fan-shaped section has a first aperture angle having a range of 10° to 50°, for example, about 24°, and a second aperture angle perpendicular to the first aperture angle, the second aperture angle having a range of 5° to 25°, and for example, substantially 12°.
According to an exemplary embodiment of the disclosure, those of the first cooling holes arranged outside the trailing edge of the blade include a second angle of between 15° and 45°, for example, of substantially 30°, with the outer surface of the blade.
According to an exemplary embodiment of the disclosure, those of the first cooling holes arranged at the trailing edge of the blade open into the environment of the blade with a 2D symmetric fan-shaped section of the bore, whereby the 2D symmetric fan-shaped section has a third aperture angle having a range of, for example, 10° to 40°, and for example, substantially 20° (e.g., ±10%)
According to an exemplary embodiment of the disclosure, those of the first cooling holes arranged at the trailing edge of the blade include a third angle of between, for example, 5° and 45°, for example, substantially 30°, with the outer surface of the blade.
According to an exemplary embodiment of the disclosure, those of the first cooling holes arranged at the trailing edge of the blade have a bore of a predetermined first length, which is subdivided into the 2D symmetric fan-shaped section and a cylindrical section of a predetermined second length, whereby the ratio of the second length and the first length is in the range of, for example, 0.2 to 0.7 (for example, substantially 0.5).
According to an exemplary embodiment of the disclosure, the first cooling holes are arranged along the pressure face in a row with a predetermined first periodicity, and the ratio between the first periodicity and the first diameter is in the range of, for example, 3 to 8 (for example, substantially 6).
According to an exemplary embodiment of the disclosure, the second cooling holes pass through the cap of the blade in a radial direction, whereby the second cooling holes can be in the form of long cylindrical bores which run obliquely upwards and include an angle of, for example, 0° to 45° (for example, substantially 30°), with the longitudinal axis of the blade.
According to an exemplary embodiment of the disclosure, the second cooling holes are arranged along the suction face in a row with a predetermined second periodicity, and the ratio between the second periodicity and the first diameter is in the range of, for example, 3 to 8 (for example, substantially 6).
According to an exemplary embodiment of the disclosure, the first cooling holes exit into the environment of the blade at a predetermined height below the upper end of the blade tip, and the ratio between the height and the first diameter is in a range between, for example, 5 and 10 (for example, substantially 6.5).
According to an exemplary embodiment of the disclosure, there are dust holes arranged along the cap between the leading edge and trailing edge, and the dust holes have a second diameter, such that the ratio between the second diameter and the first diameter is between, for example, 1.2 and 4.5.
According to an exemplary embodiment of the disclosure, the cap of the blade is bounded at the edge on its upper face by a circumferential blade crown, and the second cooling holes open into the outside area within the blade crown.
The blade can have a blade crown at the blade tip, which is bounded by a circumferential rail having a predetermined thickness. The width between the opposing rails varies with the distance along the chord line, such that, for example: t/W is between 0.05 and 0.15 for κ/κ0 between 0 and 0.3, and t/W is between 0.15 and 0.3 for κ/κ0 larger than 0.3 and up to 1.0, κ0 being the overall chord line length.
With relation to the blade tip geometry, the following exemplary ratios are preferable in exemplary embodiments:
D/W32 0.1 to 0.3 for κ/κ0 0 to 0.3;
D/W=0.1 to 0.8 for κ/κ0 >0 to 1.0;
whereas D means the depth of the tip crown and W means the width, according
The disclosure relates to a cooled gas turbine blade which can be suitable for implementation of the disclosure. The blade (10 in
Cooling channels 19a, 19b, 19c and 20 (
As shown in the exemplary embodiment in
The first and second cooling holes 25 and 27, respectively, can have the form of cylindrical bores in a simple embodiment (
In an exemplary embodiment, the first and second cooling holes (25a,b in
There can be two different kinds 25a (see
Those of the first cooling holes 25b arranged at the trailing edge 16 of the blade 10 can open into the environment of the blade 10 with a 2D (2-dimensional) symmetric fan-shaped section 30 of the bore (
As can be seen in
a shows, that the first cooling holes 25a and 25b are arranged along the pressure face 17 in a row with a (first) periodicity P1. It is desirable to choose a certain ratio P1/d between this periodicity P1 and the diameter d (see
Accordingly, the second cooling holes 27 are arranged along the suction face 18 in a row with a (second) periodicity P2. Again, the ratio P2/d1 between the second periodicity P2 and the diameter d lies in the exemplary range of 5 to 8 (for example, substantially 6).
In the exemplary embodiment illustrated in
The first cooling holes 25 open into the outside area underneath the cap 33 of the blade 10. They exit into the environment of the blade 10 at a predetermined height H below the upper end of the blade tip 11 (
The second cooling holes 27 are arranged on the opposite face and pass through the cap 33 of the blade 10 in the radial direction, opening into the outside area within the blade crown 32.
Also within the blade crown 32 dust holes 26 are provided and arranged along the cap 33 between the leading edge 15 and trailing edge 16 (
As has already been said, the blade 10 is provided with a blade crown 32 at the blade tip 11, which blade crown 32 is bounded by a circumferential rail having a predetermined thickness t (
In addition to the described cooling, the surfaces of the pressure face 17 and suction face 18 as well as the upper face of the cap 33 can be provided with a thermal protection layer (Thermal Barrier Coating TBC) 28.
Thus, it will be appreciated by those skilled in the art that the present invention can be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The presently disclosed embodiments are therefore considered in all respects to be illustrative and not restricted. The scope of the invention is indicated by the appended claims rather than the foregoing description and all changes that come within the meaning and range and equivalence thereof are intended to be embraced therein.
10 Blade (gas turbine)
11 Blade tip
12 Airfoil section
15 Leading edge
16 Trailing edge
17 Pressure face
19 Suction face
19
a,b,c Cooling channel
20 Cooling channel
21,22 Bend
23,24 Cooling hole
25,25a,25b,27 Cooling hole
26 Dust hole, particle openings
28 Thermal protective layer (Thermal Barrier Coating TBC)
29 3D fan-shaped section
30 2D fan-shaped section
32 Blade crown
33 Cap
α1,α2,α3 angle
γ angle
φ1,φ2 angle (aperture)
P1, P2 Periodicity
d,d1 Diameter
H Height
W Width
D Depth of the tip crown
t Thickness
κ Distance (along chord line)
κ0 Chord line length
Number | Date | Country | Kind |
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09155437.8 | Mar 2009 | EP | regional |
This application claims priority as a continuation application under 35 U.S.C. §120 to PCT/EP2010/053286, which was filed as an International Application on Mar. 25, 2010, designating the U.S., and which claims priority to European Application 09155437.8 filed in Europe on Mar. 18, 2009. The entire contents of these applications are hereby incorporated by reference in their entireties.
Number | Date | Country | |
---|---|---|---|
Parent | PCT/EP2010/053286 | Mar 2010 | US |
Child | 13234592 | US |