This disclosure relates to an airfoil having a shank-supported platform, for example, for an industrial gas turbine engine.
Industrial gas turbine blades include a shank that is provided between the blade root and a platform that supports the blade airfoil. One type of turbine blade includes lateral pockets provided in the shank radially beneath the platform. A rail has been used to stiffen the platform to avoid platform cracking due to thermal mechanical fatigue. The rail extends in an axial direction and radially inward from the platform in a direction opposite the airfoil.
A typical turbine blade does not include such rails. Instead, one type of military turbine blade incorporates a gusset that extends from the underside of the platform perpendicularly from the pocket toward a lateral edge of the platform. The gusset has a uniform thickness and is recessed a significant amount from the lateral edge.
In one exemplary embodiment, a blade for a gas turbine engine includes a shank interconnecting a root and a platform, and an airfoil extending radially from the shank. The shank includes a pocket with the platform overhanging the pocket. A rail extends axially along a lateral edge of the platform and extends radially inward from the platform in a direction opposite the airfoil. A gusset extends from an underside of the platform facing the pocket and in a circumferential direction between the rail and the shank.
In a further embodiment of any of the above, the airfoil includes a pressure side that is a same side of the blade as the gusset.
In a further embodiment of any of the above, the shank includes forward and aft walls spaced axially from one another. The pocket provides a depression between and adjoins the forward and aft walls.
In a further embodiment of any of the above, the gusset is arranged axially intermediately with respect to the forward and aft walls.
In a further embodiment of any of the above, the rail is normal to the platform.
In a further embodiment of any of the above, the gusset is interconnected to at least one of the rail and a surface of the pocket.
In a further embodiment of any of the above, the gusset interconnects a surface of the pocket and the rail.
In a further embodiment of any of the above, the gusset is spaced from the rail.
In a further embodiment of any of the above, the gusset is spaced from the pocket surface.
In a further embodiment of any of the above, the gusset includes a substantially uniform radial thickness.
In a further embodiment of any of the above, the gusset includes a variable radial thickness.
In a further embodiment of any of the above, the thickness is tapered radially.
In a further embodiment of any of the above, the gusset includes an axial width in the range of 0.10 to 1.00 inch (2.54 to 25.40 mm).
In another exemplary embodiment, a gas turbine engine includes compressor and turbine sections. A combustor is provided axially between the compressor and turbine sections. A turbine blade in the turbine section includes a shank interconnecting a root and a platform, and an airfoil extending radially from the shank. The shank includes a pocket with the platform overhanging the pocket. A rail extends axially along a lateral edge of the platform and extends radially inward from the platform in a direction opposite the airfoil. A gusset extends from an underside of the platform facing the pocket and in a circumferential direction between the rail and the shank.
In a further embodiment of any of the above, the gas turbine engine includes a generator operatively coupled to the gas turbine engine, which is a ground-based industrial gas turbine engine. The gas turbine engine includes a power grid operatively connected to the generator.
In a further embodiment of any of the above, the airfoil includes a pressure side that is a same side of the blade as the gusset. The shank includes forward and aft walls spaced axially from one another, and the pocket provides a depression between and adjoining the forward and aft walls. The gusset is arranged axially intermediately with respect to the forward and aft walls, the rail is normal to the platform, and the gusset is interconnected to one of the rail and a surface of the pocket.
The disclosure can be further understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:
A schematic view of an industrial gas turbine engine 10 is illustrated in
The turbine section 14 includes multiple turbine blades, one of which is illustrated at 30 in
The shank 46 includes lateral pockets 38 arranged on the pressure and suction sides of the turbine blade 30. The pressure side is illustrated in
A rail 40 extends axially in a direction A along a lateral edge of the platform 34. The rail 40 extends radially inward from the platform 34 in a direction opposite the airfoil 36, as best shown in
In the examples shown in
Referring to the turbine blade 130 of
Referring to the turbine blade 230 of
Referring to the turbine blade 330 of
Using a gusset in conjunction with a rail provides improved thermal mechanical fatigue performance by stiffening the platform. The gusset also lowers platform temperatures by acting as a heat sink by drawing heat from the platform down to the pocket where cooling air cools the gusset. The reduction in platform temperature reduces the thermal expansion of the platform, also reducing the potential for platform cracking.
Although an example embodiment has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of the claims. For that reason, the following claims should be studied to determine their true scope and content.
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International Preliminary Report on Patentability for International Application No. PCT/US2013/058289 mailed Mar. 26, 2015. |
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20140072436 A1 | Mar 2014 | US |