AXIAL STAGE INJECTION DUAL FREQUENCY RESONATOR FOR A COMBUSTOR OF A GAS TURBINE ENGINE
A gas turbine engine (202) including a secondary fuel stage (218) which also functions as a dual frequency resonator. The engine includes a combustor (210) and a casing (205) enclosing the combustor to define a volume (214). The secondary fuel stage includes a nozzle (217) sized to be effective as a transverse resonator at a high frequency. The nozzle and the volume (214) of the casing are sized to be effective as a longitudinal resonator at an intermediate frequency.
Development for this invention was supported in part by Contract No. DE-FC26-05NT42644, awarded by the United States Department of Energy. Accordingly, the United States Government may have certain rights in this invention.
FIELD OF THE INVENTIONThe invention relates to gas turbine engines, and more particularly to a resonator used to dampen resonance frequencies in a combustor of a gas turbine engine.
BACKGROUND OF THE INVENTIONA conventional combustible gas turbine engine includes a compressor section, a combustion section including a plurality of can-annular combustor apparatuses, and a turbine section. Ambient air is compressed in the compressor section and directed to the combustor apparatuses in the combustion section.
The invention is explained in the following description in view of the drawings that show:
The present inventors have recognized several limitations of the conventional resonator that is used to dampen pressure oscillations within a combustor of a gas turbine engine. For example, the inventors recognized that conventional resonators in a combustor take the form of additional components beyond those that are needed to direct and combust fluid in the combustion chamber. Based on this recognition, the present inventors developed a resonator using the existing components that direct and combust fluid in the combustion chamber, and thus eliminated the need for additional components.
The present inventors also recognized that conventional resonators in a combustor are limited to dampening one resonant frequency mode, per resonator design. Based on this recognition, the present inventors developed a resonator for a combustor, which simultaneously dampens a high frequency transverse mode and an intermediate frequency longitudinal mode, thereby reducing the number of required resonator designs to dampen multiple resonant frequency modes.
Each nozzle 217, by itself, is sized to be effective as a transverse resonator, to dampen a transverse frequency corresponding to a resonant transverse mode combustion-induced vibrations of the combustor 210. In an exemplary embodiment, as illustrated in
The combination of the nozzle 217 and the casing volume 214 (
In an exemplary embodiment, the nozzles 217, 219 at the secondary fuel stage 218 may be individually sized (i.e. length, cross-sectional area, etc.) such that a first nozzle 217 is effective as a transverse resonator at a first frequency and a second nozzle 219 is effective as a transverse resonator at a second frequency that is different than the first frequency. For example, the nozzles 217, 219 may have different lengths and/or different cross-sectional areas, such that the nozzle 217 and the nozzle 219 are sized to be effective as transverse resonators at a respective first and second frequency. Although the above example discusses that two nozzles at the secondary fuel stage may be sized differently to be effective transverse resonators at two distinct frequencies, the embodiment of the present invention is not limited to this arrangement, and includes any plurality of nozzles at the secondary fuel stage being sized differently, to be effective transverse resonators at a plurality of distinct frequencies, for example. Additionally, the length and cross-sectional areas of the nozzles 217, 219 may be sized, in addition to the casing volume 214, to ensure that the desired longitudinal frequency is dampened.
As further illustrated in
In the above embodiment, the resonator 200 dampens a wider range of the longitudinal frequency 244 (100 Hz) than the range of the transverse frequency 242 (50 Hz). Since the range of the dampened transverse frequency 242 for each nozzle design is relatively narrow, more than one nozzle design may be employed in the resonator, to increase the total range of dampened transverse frequencies. As previously discussed, multiple nozzle designs may be provided, where each nozzle design is configured to dampen a respective transverse frequency range.
While various embodiments of the present invention have been shown and described herein, it will be obvious that such embodiments are provided by way of example only. Numerous variations, changes and substitutions may be made without departing from the invention herein. Accordingly, it is intended that the invention be limited only by the spirit and scope of the appended claims.
Claims
1. A gas turbine engine comprising:
- a combustor;
- a casing enclosing the combustor and defining a volume; and
- a secondary fuel stage for delivering fuel to the combustor;
- wherein the secondary fuel stage comprises a nozzle sized to be effective as a transverse resonator;
- and wherein the nozzle and the volume of the casing are configured to be effective as a longitudinal resonator.
2. The gas turbine engine of claim 1, wherein a length of the nozzle is selected to damp vibrations of a selected frequency.
3. The gas turbine engine of claim 1, wherein the nozzle defines an opening, and wherein a cross-sectional width of the opening of the nozzle is selected to damp vibrations of a selected frequency.
4. The gas turbine engine of claim 3, wherein the nozzle is conical with a reduced cross-sectional width toward an outlet of the nozzle.
5. The gas turbine engine of claim 1, wherein a plurality of nozzles are arranged at the secondary fuel stage and wherein an angle between adjacent nozzles in a plane transverse to a longitudinal axis of the combustor is selected so that the secondary fuel stage is effective to damp a selected transverse vibration mode.
6. The gas turbine engine of claim 1, wherein the secondary fuel stage comprises a first nozzle sized to be effective as a transverse resonator at a first frequency and a second nozzle sized to be effective as a transverse resonator at a second frequency different than the first frequency.
7. The gas turbine engine of claim 1, wherein the secondary fuel stage comprises a first nozzle sized to be effective as a transverse resonator at a first frequency and wherein a third fuel stage downstream of the secondary fuel stage comprises a second nozzle sized to be effective as a transverse resonator at a second frequency different than the first frequency.
8. The gas turbine engine of claim 1, wherein the nozzle extends beyond an inner diameter of a combustion liner wall of the combustor.
9. The gas turbine engine of claim 1, wherein the nozzle does not extend beyond an inner diameter of a combustion liner wall of the combustor.
10. The gas turbine engine of claim 1, wherein a ratio of a length to a diameter of the nozzle is in a range of 0.5-5.0.
11. The gas turbine engine of claim 1, wherein a ratio of a diameter of the nozzle to a diameter of the combustor is in a range of 0.01-0.1.
12. In a gas turbine engine comprising a casing defining a volume enclosing a combustor, a resonator located at a downstream secondary fuel injection location of the combustor, said resonator comprising:
- a fuel line outlet positioned to inject fuel into an inlet of a nozzle effective to deliver fuel to the combustor through the nozzle;
- wherein the nozzle is configured to be effective as a transverse resonator for transverse vibrations in a range of 1200-4500 Hz;
- and wherein the nozzle and the volume of the casing enclosing the combustor are configured to be effective as a longitudinal resonator for longitudinal vibrations in a range of 50-150 Hz.
13. The resonator of claim 12, wherein a ratio of a length to a diameter of the nozzle is in a range of 0.5-5.0.
14. The resonator of claim 12, wherein a ratio of a diameter of the nozzle to a diameter of the combustor is in a range of 0.01-0.1.
15. The resonator of claim 12, wherein a plurality of nozzles are arranged at the downstream secondary fuel injection location and wherein an angle between adjacent nozzles in a plane transverse to a longitudinal axis of the combustor is selected so to damp a selected transverse vibration mode.
16. The resonator of claim 12, wherein the nozzle extends beyond an inner diameter of a combustion liner wall of the combustor.
17. The resonator of claim 12, wherein the nozzle does not extend beyond an inner diameter of a combustion liner wall of the combustor.
18. In a gas turbine engine comprising a casing defining a volume and a can-annular combustor disposed within the casing volume, the improvement comprising:
- a plurality of nozzles formed in a wall of the combustor to define a secondary fuel injection location;
- a fuel outlet disposed proximate an inlet of each nozzle for delivering a secondary fuel into the combustor through the nozzles;
- wherein the nozzles are configured to be effective as a resonator to dampen a transverse frequency mode of pressure oscillations developed within the combustor during operation of the engine; and
- wherein the nozzle and the casing volume are jointly configured to be effective as a resonator to dampen a longitudinal frequency mode of the pressure oscillations.
19. The gas turbine engine of claim 18, further comprising a first of the nozzles configured differently than a second of the nozzles to be effective at different respective frequencies.
20. The gas turbine engine of claim 18, further comprising:
- wherein the nozzles are configured to be effective to damp transverse vibrations in a range of 1200-4500 Hz;
- and the nozzles and the casing volume are configured to be effective to damp longitudinal vibrations in a range of 50-150 Hz.
Type: Application
Filed: Dec 18, 2013
Publication Date: Jun 18, 2015
Inventors: Jared M. Pent (Gotha, FL), Juan Enrique Portillo Bilbao (Oviedo, FL), Perry L. Johnson (Orlando, FL), Esam Abu-Irshaid (Orlando, FL), Walter R. Laster (Oviedo, FL), Scott M. Martin (Titusville, FL), Rafik N. Rofail (Oviedo, FL)
Application Number: 14/132,007