Patent Application
20050175452
(a) Field of the Invention
The present invention relates to gas turbine engines in general and in particular to turbine blades or buckets having cooling passages with a plurality of turbulators tailored for heat load.
(b) Prior Art
It is customary in turbine engines to provide internal cooling passages in turbine blades or buckets. It has also been recognized that the various stages of turbine rotors within the engines require more or less cooling, depending upon the specific location of the stage in the turbine. First stage turbine buckets usually require the highest degree of cooling because those turbine blades, located after the first vane, are the blades exposed immediately to the hot gases of combustion flowing from the combustors. It is also known that the temperature profile across each turbine blade peaks along an intermediate portion of the blade and that the temperatures adjacent the root and tip portions of the blades are somewhat lower than the temperatures along the intermediate portion.
In some cases, a plurality of cooling passages are provided within the turbine blades extending from the blade root portion to the tip portion. Cooling air from one of the stages of the compressor is conventionally supplied to these passages to cool the blades. Turbulence promoters or turbulators have been employed throughout the entire length of these passages to enhance the heat transfer of the cooling air through the passages. Thermal energy conducts from the external pressure and suction surfaces of turbine blades to the inner zones, and heat is extracted by internal cooling. Heat transfer performance in a ribbed channel primarily depends on the channel diameter, the rib configuration, and the flow Reynolds number. There have been many fundamental studies to understand the heat transfer enhancement phenomena by the flow separation caused by the ribs. In the flow past surface-mounted ribs, a boundary layer separates upstream and downstream of the ribs. These flow separations reattach the boundary layer to the heat transfer surface, thus increasing the heat transfer coefficient. The separated boundary layer enhances turbulent mixing, and therefore the heat from the near-surface fluid can more effectively get dissipated to the main flow, thus increasing the heat transfer coefficient.
The turbulence promoters used in these passageways take many forms. For example, they may be chevrons attached to side walls of the passageway, which chevrons are at an angle to the flow of cooling air through the passageway.
U.S. Pat. No. 5,413,463 to Chiu et al. illustrates turbulated cooling passages in a gas turbine bucket where turbulence promoters are provided at preferential areas along the length of the airfoil from the root to the tip portions, depending upon the local cooling requirements along the blade. The turbulence promoters are preferentially located in the intermediate region of the turbine blade, while the passages through the root and tip portions of the blade remain essentially smoothbore.
Despite the existence of these turbine blades having turbulated cooling passageways, there remains a need for blades which have improved cooling.
Accordingly, it is an object of the present invention to provide a turbine engine component having one or more cooling passageways with turbulation tailored for heat load.
The foregoing object is attained by the turbine blade of the present invention.
In accordance with the present invention, a turbine engine component having improved cooling characteristics is provided. The turbine engine component has an airfoil portion having a span, and at least one cooling passageway in the airfoil portion extending from a root portion of the airfoil portion to a tip portion of the airfoil portion. A plurality of turbulation promotion devices are placed in the at least one cooling passageway. The turbulation promotion devices have a P/e ratio which varies along the span of the airfoil portion, where P is the pitch between adjacent turbulation promotion devices and e is the height of the turbulation promotion devices.
Other details of the tailored turbulation for turbine blades of the present invention, as well as other objects and advantages attendant thereto, are set forth in the following detailed description and the accompanying drawings wherein like reference numerals depict like elements.
Referring now to
In accordance with the present invention, as shown in
As shown in
The turbine blade 10 of the present invention may be formed from any suitable metal known in the art such as a nickel based superalloy and may be cast using any suitable technique known in the art. The cooling passageways 14 and the turbulators 30 may be formed using any suitable technique known in the art such as STEM drilling or EDM milling. In a typical turbine blade, there are a plurality of cooling passages 14 along the chord of the airfoil 13.
In each of the zones A-H, the P/e ratio may be in the range of from 5 to 30. Further, the ratio of the height (e) to the diameter (D) in each of the zones may be in the range of from 0.05 to 0.30.
While the pitch in a particular zone for a particular cooling passage 14 in the blade 10 may vary from cooling passage to cooling passage, it is possible to design a blade so that the pitch in a particular zone is constant for each cooling passage.
While the turbulators 30 have been shown as being aligned, the turbulators 30 may be staggered if desired.
Further, while the turbulators 30 have been shown as having surfaces normal to the flow F through the cooling passage, the turbulators 30 could have surfaces which are at an angle with respect to the flow F, such as surfaces at an angle in the range of from 30 to 70 degrees with respect to the flow F.
As can be seen from the foregoing discussion, the present invention presents a turbine blade which better addresses the cooling needs of the turbine blade. This accomplished by varying the density of the turbulators along the span of the airfoil portion of the turbine blade.
While the cooling scheme of the present invention has been described in the context of a turbine blade, it should be recognized that the same cooling scheme could be employed in any turbine engine component having cooling passages in which the heat load varies along the length of the cooling passage.
It is apparent that there has been provided in accordance with the present invention a tailored turbulation for turbine blades which fully satisfies the objects, means, and advantages set forth hereinbefore. While the present invention has been described in the context of specific embodiments thereof, other alternatives, modifications, and variations will become apparent to those skilled in the art having read the foregoing detailed description. Accordingly, it is intended to embrace those alternatives, modifications, and variations as fall within the broad scope of the appended claims.
