Patent Application
20180230956
Disclosed embodiments are generally related to method and apparatus for a combustion turbine engine, such as gas turbine engine, and, more particularly, to method and apparatus with an arrangement of fuel ejection orifices configured for mitigating combustion dynamics that may develop in jet flames.
Certain gas turbine engines may use combustors that form a plurality of jet flames involving relatively long pre-mixing conduits towards achieving appropriate premixing of air and fuel, and meeting emissions targets. These flames can develop self-induced thermo-acoustic oscillations that may constitute an undesirable side-effect of the combustion process. For example, such thermo-acoustic oscillations may pose undue mechanical and thermal stress on combustor components.
The inventors of the present invention have recognized certain issues that can arise in the context of certain prior art combustors that may be used in combustion turbine engines, such as gas turbine engines. For example, combustors that form a plurality of jet flames that may involve relatively long pre-mixing ducts that can affect combustion dynamics due to their length relative to acoustic wavelengths of the combustor system. One non-limiting example of such combustors may be a jet flame combustor, which can develop self-induced thermoacoustic oscillations in the jet flames, as may be caused by respective fluctuations in the mass flow of fuel and air that in turn may cause pockets of fuel/air mixtures with distinctive differences in equivalence ratio (e.g., rich/lean pockets). These flame oscillations can detrimentally affect combustion dynamics in the jet flames and can further limit the ability to tune the combustor system towards achieving lower levels of NOx emissions.
In view of such recognition, the present inventors propose an improved fuel injector comprising an array of fuel-ejection locations strategically arranged to form oscillatory interference patterns (e.g., destructive wave interference) effective to reduce the magnitude of the differences of equivalence ratio in the pockets of fuel/air mixtures that may be formed in the pre-mixing ducts and thus resulting in more homogenous air/fuel mixture exiting the ducts and thus relatively more steadier flames. That is, flames with a reduced level of self-induced oscillations. The proposed fuel injector is believed to be effective to spread the convective time of equivalence ratio perturbations that otherwise would develop in the pockets of fuel/air mixtures in the pre-mixing ducts, and thus the proposed fuel injector effectively detunes the combustor from the system acoustics, which in turn is conducive to a wider operating envelope that provides the ability to tune the combustor system towards achieving lower levels of NOx emissions.
In the following detailed description, various specific details are set forth in order to provide a thorough understanding of such embodiments. However, those skilled in the art will understand that embodiments of the present invention may be practiced without these specific details, that the present invention is not limited to the depicted embodiments, and that the present invention may be practiced in a variety of alternative embodiments. In other instances, methods, procedures, and components, which would be well-understood by one skilled in the art have not been described in detail to avoid unnecessary and burdensome explanation.
Furthermore, various operations may be described as multiple discrete steps performed in a manner that is helpful for understanding embodiments of the present invention. However, the order of description should not be construed as to imply that these operations need be performed in the order they are presented, nor that they are even order dependent, unless otherwise indicated. Moreover, repeated usage of the phrase “in one embodiment” does not necessarily refer to the same embodiment, although it may. It is noted that disclosed embodiments need not be construed as mutually exclusive embodiments, since aspects of such disclosed embodiments may be appropriately combined by one skilled in the art depending on the needs of a given application.
The terms “comprising”, “including”, “having”, and the like, as used in the present application, are intended to be synonymous unless otherwise indicated. Lastly, as used herein, the phrases “configured to” or “arranged to” embrace the concept that the feature preceding the phrases “configured to” or “arranged to” is intentionally and specifically designed or made to act or function in a specific way and should not be construed to mean that the feature just has a capability or suitability to act or function in the specified way, unless so indicated.
As may be appreciated in
In one non-limiting embodiment, a spacing (e.g., labelled ΔL) between the first and second axial locations is arranged to effect oscillatory interference patterns (e.g., destructive wave interference) in pockets 44 comprising mixtures of air and fuel that flow towards a downstream outlet 45 of pre-mixing passage 24. As will be appreciated by those skilled in the art, destructive wave interference occurs when the phase shift between superimposed waves is an odd multiple of π. In one non-limiting embodiment, the spacing between rows R1 and R2 of fuel ejection orifices may be selected to introduce a phase shift Δφ, where Δφ=π*n, where n=1, 3, 5, 7, and so on and so forth. As will be appreciated by those skilled in the art, this phase shift (in the time domain) is a function of the local velocity profile and the distance between the premix passage and the flame. The phase shift introduced due to the spacing between rows R1 and R2 of fuel ejection orifices may be tuned to a given frequency of interest. It will be appreciated that aspects of the present invention are neither limited to two rows of fuel ejection orifices nor to phase shifts based on an odd multiple of π since these parameters may be tailored based on the needs of a given application.
The oscillatory interference patterns are effective to promote homogeneity in the mixtures of air and fuel and dampen thermoacoustic oscillations in a flame 46 formed upon ignition of the mixtures of air and fuel. For example, in lieu of such pockets being made up of either fuel-rich or fuel-lean pockets, as would occur in certain prior art combustors, because of the destructive interference resulting from the relative axial positioning of rows R1 and R2 of the fuel ejection orifices, such pockets may now be advantageously characterized as effectively comprising both a fuel-rich (FR) zone and a fuel-lean (FL) zone, as conceptually indicated
In one non-limiting embodiment, the respective rows of fuel ejection orifices R1, R2 may comprise circumferentially-extending rows of fuel ejection orifices respectively spanning at least respective portions of a perimeter of the fuel-injecting lance. In one non-limiting embodiment, the circumferentially-extending row of fuel ejection orifices at the first axial location may comprise fuel ejection orifices configured for fuel-rich injection, and the circumferentially-extending row of fuel ejection orifices at the second axial location may comprises fuel ejection orifices configured for fuel-lean injection. Alternatively, the circumferentially-extending row of fuel ejection orifices at the first axial location may comprise fuel ejection orifices configured for fuel-lean injection, and the circumferentially-extending row of fuel ejection orifices at the second axial location may comprise fuel ejection orifices configured for fuel-rich injection.
For example, in one non-limiting embodiment, as schematically represented in
In another non-limiting embodiment, as schematically represented in
As schematically illustrated in
It will be appreciated that aspects of the present invention are not limited to any particular pattern for the fuel ejection orifices in a given fuel injector since such patterns may be customized at the fuel injector level. Additionally, it will be appreciated that the designer has the flexibility to customize at the burner and/or the combustor system level the patterns for the fuel ejection orifices. For example, let us say that a given burner utilizes ten fuel injectors, then the respective patterns for the fuel ejection orifices in the ten fuel injectors need not be identical to one another since such patterns may be customized at the burner level. In yet another example, let us say that a given burner system in a gas turbine utilizes an arrangement of seven burners, then the patterns for the fuel ejection orifices in the seven burners in that burner arrangement need not be identical to one another since such patterns may be customized at the burner system level. It will be further appreciated that aspects of the present invention are not limited to any particular shape for the fuel ejection orifices. Non-limiting examples may be a circular shape, an elongated shape, an oval shape, a combination of two or more of the foregoing shapes.
In operation, disclosed embodiments are believed to provide a cost effective and reliable combustor apparatus with superior air-fuel mixing capability conducive to flames with a reduced level of self-induced oscillations. Additionally, disclosed embodiments are believed to provide an elegant means for detuning the combustor from system acoustics, which in turn is conducive to a wider operating envelope that provides the ability to tune the combustor system towards achieving lower levels of NOx emissions.
While embodiments of the present disclosure have been disclosed in exemplary forms, it will be apparent to those skilled in the art that many modifications, additions, and deletions can be made therein without departing from the spirit and scope of the invention and its equivalents, as set forth in the following claims.
| Filing Document | Filing Date | Country | Kind |
|---|---|---|---|
| PCT/US2015/046498 | 8/24/2015 | WO | 00 |
