Patent Application
20160115799
The subject matter disclosed herein relates to the art of turbomachines and, more particularly, to a method of forming turbulators on a turbomachine surface.
Turbomachine systems typically include a turbomachine coupled to an intake system and a load. The turbomachine typically includes a compressor portion and a turbine portion. An airstream passes through the intake system into the compressor portion. The compressor portion forms a compressed air stream that is introduced into the turbine portion. In a gas turbomachine, a portion of the compressed airstream mixes with products of combustion in a combustor assembly forming a hot gas stream that is introduced into the turbine portion through a transition piece. In some cases, turbomachine gases may pass over turbulators to enhance various flow and operational characteristics.
The hot gas stream flows from a transition piece fluidically connecting the combustor assembly and the turbine portion. The hot gases passing from the transition piece flow toward a first stage of the turbine portion. The hot gases flow over a first stage nozzle prior to impacting first stage rotor blades. The first stage nozzle conditions and directs the hot gases toward the first stage rotor blades. The hot gases expand through additional stages of the turbine portion, each having associated rotor blades, before passing to an exhaust system.
The rotor blades are generally connected to a wheel which, in turn, may be connected to a shaft. Typically, the shaft is operatively connected to a load. The hot gas stream imparts a force to the rotor blades causing rotation of the shaft. The rotation of the shaft is transferred to the rotor. Thus, the turbine portion converts thermal energy from the hot gas stream into mechanical/rotational energy that is used to drive the load. The load may take on a variety of forms including a generator, a pump, an aircraft, a locomotive, or the like.
According to one aspect of an exemplary embodiment, a method of forming a plurality of turbulators on a turbomachine surface includes depositing a portion of material on the turbomachine surface, forming a first portion of the plurality of turbulators, adding additional material to the first portion, and establishing a desired dimension of the plurality of turbulators.
According to another aspect of an exemplary embodiment, a turbomachine includes a compressor portion, including a compressor surface, and a turbine portion operatively connected to the compressor portion. The turbine portion includes a turbine surface. A combustor is fluidically connected to the compressor portion and the turbine portion. The combustor includes a combustor surface. At least one of the compressor surface, turbine surface, and combustor surface includes a plurality of turbulators. Each of the plurality of turbulators is formed from material deposited onto at least one of the compressor surface, turbine surface, and combustor surface.
According to yet another aspect of an exemplary embodiment, a turbomachine system includes a compressor portion including a compressor surface and a turbine portion operatively connected to the compressor portion. The turbine portion includes a turbine surface. An intake system is fluidically connected to the compressor portion. A load is operatively connected to one of the compressor portion and the turbine portion. A combustor is fluidically connected to the compressor portion and the turbine portion. The combustor includes a combustor surface. At least one of the compressor surface, turbine surface, and combustor surface includes a plurality of turbulators. Each of the plurality of turbulators is formed from material deposited onto at least one of the compressor surface, turbine surface, and combustor surface.
These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
With initial reference to
Combustor 22 includes a combustor liner 40. As shown in
In further accordance with an exemplary embodiment, material 64 may be embodied in a welding electrode shown as an electrically conductive wire 68 that is deposited onto outer surface 50 through a welding process. More specifically, electrically conductive wire 68 may be a consumable electrode dispensed from a welding member shown in the form of a metal-inert-gas (MIG) gun 70 positioned proximate to outer surface 50. Alternatively, material 64 may be embodied in a non-consumable electrode such as TIG or plasma arc welding. In still further accordance with an aspect of an exemplary embodiment, combustor liner 40 is rotated about a first axis 78 while material 64 is deposited onto outer surface 50. After forming one of the plurality of turbulators 60, MIG gun 70 translates, along a second axis 80, to form another of the plurality of turbulators 60, as will be detailed more fully below. Second axis 80 is angled relative to first axis 78 and generally follows an outer profile (not separately labeled) of combustor liner 40.
As shown in
At this point it should be understood that the exemplary embodiments describe a method of adding one or more turbulators to a turbomachine surface. More specifically, in contrast to prior art processes in which material is removed or subtracted from a surface, the exemplary embodiments add material to a turbomachine surface to form one or more turbulators. The addition of material not only reduces or eliminates significant waste formed when employing machining techniques, but also reduces manufacturing time. Further, by adding material, the turbulators may be formed having a number of geometries previously unattainable, in a cost effective manner, through subtractive processes such as machining. It should also be appreciated that the number, size, shape and pattern of the turbulators may vary. For example, turbulator dimensions may vary depending on desired heat transfer characteristics. Further, while shown as being added to an outer surface of a combustor liner, turbulators may be formed on virtually any turbomachine surface including compressor surfaces and turbine surfaces.
While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
