Patent Application
20190093564
Combustors, such as those used in industrial gas turbines, for example, mix compressed air with fuel and expel high temperature, high pressure gas downstream. The energy stored in the gas is then converted to work as the high temperature, high pressure gas expands in a turbine, for example, thereby turning a shaft to drive attached devices, such as an electric generator to generate electricity.
As the air/fuel mixture combusts, the hot gas that is generated creates fluctuations in pressure. These pressure fluctuations at certain frequencies (e.g., 100-5000 Hz) create acoustic pressures through the system. Accordingly, the combustion system is susceptible to High Cycle Fatigue (HCF) resulting from these combustion dynamics. The inability to account for the frequency of oscillation will jeopardize the structural integrity of the combustion system which may lead to a catastrophic failure.
There are knowns ways of preventing the excitation of natural frequency within the system. Acoustic pressure fluctuations that can generate natural frequencies may be reduced by redesigning the hardware, changing air splits, or adding external resonators to the system. However, in large applications such as an industrial gas turbine, for example, this can result in adding significant cost or reduction of the combustion system performance as extensive time for tests and modifications are needed. Additionally, if not designed properly, external resonators for this purpose can reduce the combustor performance as the resonator will need air for damping. Inefficient design and misplacement of the external resonators will take away air needed for combustion, thereby decreasing the efficiency of the combustion. Such may result in increased emission levels, metal temperature, and thermal stresses, all of which will affect the life and performance of the structure of the system.
Resonators are usually evaluated based on impedance, admittance and the amount of absorbed acoustic energy. The design of a resonator is usually based on the observed frequency. Features such as resonator volume, inner and out holes, purge air are usually adjusted to capture the desired frequency and damping. Additionally, the design of the resonator is typically performed with disregard to cooling or performance requirements.
Just as important as the design of the resonator itself, placement of the resonator within the combustion system. Typically, resonator or damper location is based on a set of criteria that is not dynamically integrated with the system. The axial or tangential placements of the resonator in the combustion system is usually based on experience or testing data. However, placing the resonator at the wrong location can impact performance and cooling of the resonator. This approach, however, may become unrealistic and costly due to extensive trial and error testing.
The present disclosure is directed to improved resonator design and procedures for design and placement thereof based on resonator impact on the system instability rather than focusing on sets of stand-alone criteria for the resonator, optimizing the impact of the resonator on other frequencies that cannot be measured if the resonator is designed separately, thereby maximizing the resonator performance and increasing efficiency.
In one embodiment of the invention, a system for designing a resonator to dampen acoustic energy in a combustion system includes a design module configured to generate a resonator design to dampen a target frequency and acceptable damping, a system analysis module configured to evaluate the resonator design within a modeled combustion system environment to determine a damping effect of the resonator design on the combustion system as a whole, and a system optimization module configured to adjust the resonator design to optimize an overall effect on the combustion system as a whole.
In another embodiment of the invention, a computer-implemented method for damping acoustic energy in a combustion system includes the steps of designing a resonator on a computer to dampen a target frequency, analyzing the resonator on the computer to determine a damping effect of the design, evaluating the resonator within a modeled combustion system environment on the computer to determine a damping effect of the design on the combustion system as a whole, adjusting the design of the resonator on the computer to optimize an overall effect on the combustion system as a whole, and generating a finalized resonator design having the overall effect on the combustion system as a whole.
In yet another embodiment of the invention, a computer program product includes computer executable instructions that, when executed by a computer, causes the computer to perform the steps of designing a resonator on a computer to dampen a target frequency, analyzing the resonator on the computer to determine a damping effect of the design, evaluating the resonator within a modeled combustion system environment on the computer to determine a damping effect of the design on the combustion system as a whole, adjusting the design of the resonator on the computer to optimize an overall effect on the combustion system as a whole, and generating a finalized resonator design having the overall effect on the combustion system as a whole.
Various embodiments of an acoustic resonator in a combustion system and a method of designing the same are described. It is to be understood, however, that the following explanation is merely exemplary in describing the devices and methods of the present disclosure. Accordingly, any number of reasonable and foreseeable modifications, changes, and/or substitutions are contemplated without departing from the spirit and scope of the present disclosure.
Resonator or damper location in combustion systems has typically been based on a set of criteria that is not dynamically integrated with the system. Axial or tangential locations of the resonator depends on experience with combustion systems and testing data. Placing the resonator at the wrong location can impact performance and cooling of the resonator.
External resonators are expensive and can cause inefficiencies when air goes through the resonator rather than through the combustion system, thereby increasing emissions. Further, cold air mixing with hot gas causes thermal stresses, thereby weakening the structural integrity of the components in the combustion system. In accordance with the present disclosure, resonators are placed on the outside of the combustion system by forming holes in the liner. By considering the size and shape of the holes, the amount of airflow, and shell volume, a resonator is created to dampen a target frequency without affecting the emissions efficiencies of the combustion system.
The acoustic model for the whole combustion system in accordance with the present disclosure gives expected frequencies. In particular, frequency plot of the combustion system is used to identify a frequency with unstable energy and a mode for that frequency is plotted to identify the anti-node type and location (S40-1). The resonator design is then placed at or near the identified anti-node and evaluated for damping effect with minimum cooling requirements (S40-2). The entire combustion system with the resonator design in place is then evaluated for effects on other frequencies in the system (S40-3).
Once a resonator design and placement of the resonator in the combustion system has been evaluated, the design and placement of the resonator is evaluated for optimization (S50). For example, placement of the resonator may be adjusted to provide slightly less damping for the sake of increasing the effect on cooling by re-evaluating the location of the anti-node (S50-1), effects of cooling (S50-2), and effects on other frequencies (S50-3). Once all evaluations have been performed, the design and placement of the resonator is finalized (S60). The effects of the optimization according to the present disclosure is illustrated in
The acoustic model 160 provides the foundation for each of the resonator tool module 120, the resonator analysis module 130, the combustion system analysis module 140, and the system optimization module 150 to be able to perform the necessary design and analyses. In particular, the acoustic model 160 includes models of the mode shape of the acoustic energies and frequencies that are generated within the combustion system, models of the damping effects of the resonator, and models of the resonator and combustion system components, such as heat source, heat transfer characteristics, friction/damping effects, etc. For example, the acoustic model 160 includes mathematical modeling of the damping impact or effect of the resonator on the combustion system as a whole rather than as a stand-alone design, as shown in Equation (1) below:
Additionally, the damping model above employs non-linear effects that account for saturation such that saturation is predicted to prevent resonator over-damping.
By modeling both the driving or energy source and the damping source, the combustion system analysis module 140 can determine whether the resonator would effectively dampen the targeted acoustic energy, have no significant effect, or make the combustion system even more unstable. Based on the acoustic models generated within the combustion system, the overall impact of the design resonator is assessed and optimization is achieved quickly and cost efficiently, reducing testing time from trial and error approaches used in the past.
Some of the advantages of the exemplary embodiments include: reduced testing cost related to optimization of the resonator location, reduced testing cost by optimizing the inner and outer hole sizes of the resonator, reduced uncertainty of the resonator design as it is assessed on the direct impact against the instability of the combustion system rather than on stand-alone criteria, and optimization of the resonator location, axially or tangentially, so as to achieve maximum damping with minimum impact of system performance.
The breadth and scope of the present disclosure should not be limited by any of the above-described exemplary embodiments, but should be defined only in accordance with the following claims and their equivalents. For example, each of the modules in the RDS 100 may be stand-alone software applications or one or more module may be combined. Further, RDS 100 may be implemented on a general purpose computer, or on a specialized device, and may be stand-alone or networked to take advantage of distributed processing on multiple computers. Moreover, the above advantages and features are provided in described embodiments, but shall not limit the application of the claims to processes and structures accomplishing any or all of the above advantages.
Additionally, the section headings herein are provided for consistency with the suggestions under 37 CFR 1.77 or otherwise to provide organizational cues. These headings shall not limit or characterize the invention(s) set out in any claims that may issue from this disclosure. Further, a description of a technology in the “Background” is not to be construed as an admission that technology is prior art to any invention(s) in this disclosure. Neither is the “Brief Summary” to be considered as a characterization of the invention(s) set forth in the claims found herein. Furthermore, any reference in this disclosure to “invention” in the singular should not be used to argue that there is only a single point of novelty claimed in this disclosure. Multiple inventions may be set forth according to the limitations of the multiple claims associated with this disclosure, and the claims accordingly define the invention(s), and their equivalents, that are protected thereby. In all instances, the scope of the claims shall be considered on their own merits in light of the specification, but should not be constrained by the headings set forth herein.
