Patent Application
20080181784
A gas turbine blade is disclosed.
It is known, with cooled blades of gas turbines, to blow out cooling air at the blade tip, which for example promotes improved cooling of the seals which are arranged there. The cross sections of these outlet openings are generally dimensioned smaller than those of the cooling air passages. Therefore, they serve as restricting points and limit the mass flow of the cooling fluid which is blown out. The outlet openings customarily have circular or elliptical cross sections, and do not coincide with the cross-sectional shape of the cooling passage which guides the cooling air to the outlet opening. The abrupt cross-sectional change which consequently exists, results in unfavorable flow patterns which inter alia lead to increased pressure losses and locally increased material temperatures.
An exemplary gas turbine blade of the type referred to in the introduction is disclosed so that the disadvantages of the prior art are avoided. More specifically, the gas turbine blade is to be disclosed in such a way that the heat transfer is evened out on the cooling side, and in this way uneven temperature distributions, with thermal stresses which shorten the service life, are avoided.
This, in addition to other advantageous effects, the gas turbine blade is able to achieve. In the blade, the contour of the outlet opening of the cooling air passage, which extends along the leading edge, is designed geometrically similar to the cross section of the cooling air passage. The result of this is that the cross-sectional transitions during the through-flowing of cooling air from the cooling air passage into the outlet opening are minimized. Eddy zones of the cooling air and deviations of the flow direction of the cooling air which is blown out, with their negative effects, are therefore avoided.
In one development of the blade, the cross-sectional area of the outlet opening is smaller than the cross-sectional area of the cooling air passage. As a result, the outlet opening can act as a restricting point and consequently serve for limiting the mass flow. That is to say, a rib is arranged in the region of the outlet opening. In one embodiment of the disclosure, the distance of the contour line of the outlet opening from the outer contour of the blade airfoil in the region of the leading edge of the blade airfoil, assumes values of between 138% and 162% of the local wall thickness of the wall of the blade airfoil. That is to say, the height of the rib in the region of the leading edge of the blade airfoil is 38% to 62% of the local wall thickness. In the region of the suction-side wall and/or the pressure-side wall of the blade airfoil, the distance of the contour line of the outlet opening from the outer contour of the blade airfoil assumes values of 113% to 138% of the local wall thickness of the wall of the blade airfoil. The height of the rib, therefore, in this region is 13% to 38% of the local wall thickness. In the region of the partition inside the blade, which for example separates the cooling air passage, which extends along the leading edge, from other cooling air passages, the height of the rib in one embodiment lies within the range of 0% to 225% of the wall thickness of the wall of the blade airfoil. These geometric specifications can naturally be applied independently of each other or in combination. The wall thickness of the wall of the blade airfoil in this case can vary in the flow direction of the blade airfoil; in one embodiment of the disclosure the wall thickness of the wall of the blade airfoil in the region of the outlet opening is constant.
The exemplary cooling air passage has an inlet opening which is arranged at the blade root. In this case, in one embodiment, fresh cooling air is supplied at the blade root and flows along the leading edge of the blade airfoil inside the blade airfoil to the blade tip, and flows out there through the outlet opening. In one development of the blades which are specified here, the blade is especially designed in a way in which it is purely convectively cooled in the region of the cooling passage. That is to say, there are no openings through which cooling air, for example as film cooling air, can reach the outer side of the blade airfoil. The entire cooling air mass flow which flows into the cooling air passage, therefore, flows out again through the outlet opening.
Blades of the previously described type are preferably used in gas turbines, as component parts of a rotor and/or of a stator.
An exemplary embodiment is illustrated in the drawings. In detail, in the drawings:
All the figures are much simplified and only serve for better understanding of the disclosure; they are not to be considered as limitation of the disclosure.
In
In modern gas turbo groups with high hot gas temperatures, the turbine blades of at least the first turbine stages are designed in a way in which they are cooled. An example of such a cooled turbine blade 6 is shown in
The region of the outlet opening 611 is shown enlarged in
Although the disclosure was explained in detail above with reference to an exemplary embodiment, it is obvious to the person skilled in the art that this exemplary embodiment does not limit the disclosure. In light of the preceding description, further embodiments of the disclosure, which are contained within the scope of the patent claims, present themselves to a person skilled in the art.
| Number | Date | Country | Kind |
|---|---|---|---|
| 2005110990 | Apr 2005 | RU | national |
This application claims priority under 35 U.S.C. §119 to Russian Application 2005110990 filed in Russia on 14 Apr. 2005, and as a continuation application under 35 U.S.C. §120 to PCT/EP2006/061163 filed as an International Application on 30 Mar. 2006 designating the U.S., the entire contents of which are hereby incorporated by reference in their entireties.
| Number | Date | Country | |
|---|---|---|---|
| Parent | PCT/EP2006/061163 | Mar 2006 | US |
| Child | 11907420 | US |
