Patent Application
20150047358
The subject matter disclosed herein relates to the art of turbomachines and, more particularly to an inner barrel member with an integrated diffuser for a gas turbomachine.
In general, gas turbine engines combust a fuel/air mixture that releases heat energy to form a high temperature gas stream. The high temperature gas stream is channeled to a turbine portion via a hot gas path. The turbine portion converts thermal energy from the high temperature gas stream to mechanical energy that rotates a turbine shaft. The turbine portion may be used in a variety of applications, such as for providing power to a pump or an electrical generator or other mechanical device.
According to one aspect of an exemplary embodiment, an inner barrel member for a gas turbomachine includes a body having an outer surface, an inner surface and one or more radial flow splitters provided on the outer surface. The one or more radial flow splitters are configured and disposed to be arranged along a combustor centerline at a combustion flow outlet radially inwardly of a transition piece.
According to another aspect of the exemplary embodiment, a gas turbomachine includes a compressor portion having a first inner casing and a second inner casing, and a turbine portion mechanically linked to the compressor portion. A combustor assembly includes a plurality of combustors that fluidically connect the compressor portion and the turbine portion. Each of the plurality of combustors includes a transition piece. An inner barrel member mechanically and fluidically connects the first inner casing and the second inner casing. The inner barrel member includes a body having an outer surface, an inner surface, and one or more radial flow splitters provided on the outer surface. Each of the one or more radial flow splitters is arranged along a combustor centerline of one of the plurality of combustors radially inwardly of the transition piece of one or more of the combustors.
In accordance with yet another exemplary embodiment, a gas turbomachine system includes a compressor portion having a first inner casing and a second inner casing, an intake system fluidically connected to the compressor portion, a turbine portion mechanically linked to the compressor portion, and an exhaust system fluidically connected to the turbine portion. A driven member is mechanically linked to the compressor portion and the turbine portion and a combustor assembly including a plurality of combustors fluidically connects the compressor portion and the turbine portion. Each of the plurality of combustors includes a transition piece. An inner barrel member mechanically and fluidically connects the first inner casing and the second inner casing. The inner barrel member includes a body including an outer surface and an inner surface and one or more radial flow splitters provided on the outer surface. Each of the one or more radial flow splitters is arranged along a combustor centerline of one of the plurality of combustors radially inwardly of the transition piece of one or more of the combustors.
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.
A turbomachine, in accordance with an exemplary embodiment, is indicated generally at 2 in
As shown in
Air enters into compressor portion 4 through an intake system 50 (
As best shown in
In accordance with an aspect of the exemplary embodiment, each radial flow splitter 90 is materially, integrally formed with outer surface 33 of inner barrel member 35. However, it should be understood that radial flow splitters 90 may also be attached to outer surface 33. As shown in
At this point it should be understood that the exemplary embodiments describe an inner barrel member having radial flow splitters including tapered surfaces that guide compressor air between adjacent transition piece outlets into products of combustion passing from each combustor. Integrating flow splitters into the inner barrel member creates a more favorable flow field about the combustors, enhances combustion dynamics, improves performance, and reduces emissions. Further, the incorporation of radial flow splitters to the inner barrel member enables a turbomachine having a shorter diffusing section, to exhibit performance characteristics of longer turbomachine. Moreover, aligning the radial flow splitters with a centerline of each combustor promotes more complete mixing of compressed air passing between adjacent combustors and products of combustion exiting each transition piece outlet. It should also be understood that there need not be a radial flow splitter associated with each transition piece.
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.
