Gas turbine engine with resonator rings

A gas turbine engine has a resonator ring that is formed by two circumferentially extending rings. The first and second circumferentially extending rings have located within them baffles. Both the first ring and the second ring are able to mitigate acoustic frequencies generated by the gas turbine engine.

BACKGROUND

Disclosed embodiments are generally related to gas turbine engines and, more particularly to resonators used in gas turbine engines.

2. Description of the Related Art

A gas turbine engine typically has a compressor section, a combustion section having a number of combustors and a turbine section. Ambient air is compressed in the compressor section and conveyed to the combustors in the combustion section. The combustors combine the compressed air with a fuel and ignite the mixture creating combustion products. The combustion products flow in a turbulent manner and at a high velocity. The combustion products are routed to the turbine section via transition ducts. Within the turbine section are rows of vane assemblies. Rotating blade assemblies are coupled to a turbine rotor. As the combustion product expands through the turbine section, the combustion product causes the blade assemblies and turbine rotor to rotate. The turbine rotor may be linked to an electric generator and used to generate electricity.

During the operation of gas turbine engines strong forces are generated that can impact the structure of the gas turbine engine. Accommodating these forces to continue to provide optimal operation is important for the continued operation of the gas turbine engine.

SUMMARY

Briefly described, aspects of the present disclosure relate to resonators.

An aspect of the disclosure may be a gas turbine engine having a combustor located within a combustor basket. The gas turbine engine may also have a resonator ring connected to the combustor basket; wherein the resonator ring comprises a first ring and a second ring, wherein the first ring is located upstream of the second ring; wherein the first ring comprises a first perimeter wall and a second perimeter wall extending in a circumferential direction, wherein located between the first perimeter wall and the second perimeter wall is a first bottom portion and a first top portion, wherein the first bottom portion has a first plurality of holes, wherein the first top portion has a second plurality of holes. Located between the first perimeter wall and the second perimeter wall is a first plurality of baffles, wherein each of the first plurality of baffles extends orthogonally with respect to the first perimeter wall and the second perimeter wall. The second ring comprises the second perimeter wall and a third perimeter wall extending in a circumferential direction, wherein located between the second perimeter wall and the third perimeter wall is a second bottom portion and a second top portion, wherein the second bottom portion has a third plurality of holes, wherein the second top portion has a fourth plurality of holes; and further wherein located between the second perimeter wall and the third perimeter wall is a second plurality of baffles, wherein each of the second plurality of baffles extends orthogonally with respect to the second perimeter wall and the third perimeter wall.

Another aspect of the disclosure may be a resonator ring connectable to a combustor basket comprising a first ring and a second ring, wherein the first ring is located upstream of the second ring. The first ring comprises a first perimeter wall and a second perimeter wall extending in a circumferential direction, wherein located between the first perimeter wall and the second perimeter wall is a first bottom portion and a first top portion, wherein the first bottom portion has a first plurality of holes, wherein the first top portion has a second plurality of holes. Located between the first perimeter wall and the second perimeter wall is a first plurality of baffles, wherein each of the first plurality of baffles extends orthogonally with respect to the first perimeter wall and the second perimeter wall. The second ring comprises the second perimeter wall and a third perimeter wall extending in a circumferential direction, wherein located between the second perimeter wall and the third perimeter wall is a second bottom portion and a second top portion, wherein the second bottom portion has a third plurality of holes, wherein the second top portion has a fourth plurality of holes; and further wherein located between the second perimeter wall and the third perimeter wall is a second plurality of baffles, wherein each of the second plurality of baffles extends orthogonally with respect to the second perimeter wall and the third perimeter wall.

DETAILED DESCRIPTION

The present inventors have recognized certain drawbacks that affect at least some existing resonators used in gas turbine engines. These drawbacks tend to add complexity and costs while lessening the operational reliability of the gas turbine engine. For example, these existing resonators tend to involve a relatively high cost of manufacturing and a relatively low use life. For example, a gas turbine engine may involve multiple such resonators or resonator boxes to achieve a desired acoustic damping. These resonator boxes may require extensive machining, multiple points of welding and difficult welding locations in order to install and achieve appropriate structural integrity. Furthermore, complex shapes may be required in order to provide cooling in the spaces between the resonator boxes thus complicating the design of the gas turbine engine.

In view of such recognition, the present inventors propose an innovative resonator ring structure that is expected to avoid or least reduce the foregoing drawbacks. Without limitation, disclosed embodiments of the resonator ring may be formed with more than one ring and may employ baffles in order to form improved resonator boxes. In the resonator ring disclosed herein the resonator boxes share walls, formed by the baffles. The sharing of walls removes the need for using complex features for cooling, thereby reducing the complexity of the design. Furthermore, difficult machining and welding of the resonator boxes are reduced thereby decreasing the overall cost of manufacture. Additionally, the use of the resonator ring permits improved cooling of the resonator ring and resonator boxes, thereby improving the life span of the components and reducing replacement of parts.

It should be understood that additional benefits may be achieved by the features disclosed here and not limited to those discussed above.

To facilitate an understanding of embodiments, principles, and features of the present disclosure, they are explained hereinafter with reference to implementation in illustrative embodiments. Embodiments of the present disclosure, however, are not limited to use in the described systems or methods.

FIG. 1shows a view of the gas turbine engine5. The combustor6is located within the combustor basket7.FIG. 2shows a close up view of the combustor basket7and the resonator ring10. The combustor6produces combustion products that are transmitted downstream through the combustor basket7and the resonator ring10into the transition system. From there combustion products flow downstream to the turbine section and may be used to generate electricity.

The resonator ring10is able to control for various acoustical frequencies generated by the combustor6during operation of the gas turbine engine5. Furthermore, the resonator ring10described herein is able to facilitate the ease with which it can be created and further improve the cooling that occurs in the resonator ring10.

FIG. 3is a view of the resonator ring10that permits viewing of the interior of the resonator ring10. The resonator ring10has first ring30and a second ring31. The second ring31is located downstream from the combustor6. While the current embodiment shows a first ring30and a second ring31it should be understood that more or fewer rings may be employed. The number of rings employed may occur in accordance with the ideas set forth herein, depending on the size, shape and complexity needed for a particular gas turbine engine.

The first ring30is formed by a first perimeter wall12and a second perimeter wall14that extends circumferentially around the axis of the combustor6and combustor basket7. The second ring31is formed by the second perimeter wall14and a third perimeter wall16that extends circumferentially around the axis of the combustor6and combustor basket7. The first ring30and the second ring31may be formed together on a single unitary piece in order to form the resonator ring10. However, it should be understood that they may be formed by separate pieces welded, brazed or joined in other ways understood by the skilled artisan.

The first ring30has a first bottom portion11that is bordered by the first perimeter wall12and second perimeter wall14. The first bottom portion11extends circumferentially around the axis. The second ring31has a second bottom portion13that is bordered by the second perimeter wall14and the third perimeter wall16. The second bottom portion13also extends circumferentially around the axis.

Referring toFIG. 4, during assembly a first top portion26will be placed over the space formed by the first bottom portion11, the first perimeter wall12and the second perimeter wall14. Additionally a second top portion27will be placed over the space formed by the second bottom portion13, the second perimeter wall14and the third perimeter wall16. The first top portion26and the second top portion27may be formed from single pieces or be formed from separate component pieces.

Referring back toFIG. 3, a plurality of first baffles20are located within the first ring30. A plurality of second baffles22are located within the second ring32. First baffles20extend orthogonally between the first perimeter wall12and the second perimeter wall14. Second baffles22extend orthogonally between the second perimeter wall14and the third perimeter wall16. While first baffles20and second baffles22are shown extending orthogonally, it should be understood that first baffles20and second baffles22may also extend at other angles and directions between the first perimeter wall12, second perimeter wall14and third perimeter wall16. With the installation of the first baffles20and second baffles22and the instalment of the first top portion26and the second top portion27, first resonator boxes24and second resonator boxes25are formed in the first ring30and the second ring31.

In the embodiment shown inFIG. 3, the first ring30has a number of first resonator boxes24that is different than the number of second resonator boxes25formed the second ring31. Furthermore the overall size and volume of the first resonator boxes24are different than the second resonator boxes25. This permits the first resonator boxes24in the first ring30to handle different acoustical frequencies than the second resonator boxes25in the second ring31.

In the resonator ring10shown, the first baffles20have a length L1that is less than a length L2of the second baffles22. This results in the width W1of a first resonator box24being less than the width W2of a second resonator box25. As shown, the height H1of the first baffle20, is the same as the height H2of the second baffle22. However, it should be understood that the heights of the first baffles20and the second baffles22may be different thereby potentially forming different volumes.

The distance D1between two adjacent first baffles20is greater than a distance D2between two adjacent second baffles22. Thus the resonator box24appears thinner than the resonator box25, which appears squatter inFIG. 3. Furthermore, the area formed between adjacent first baffles20is less than an area formed between adjacent second baffles22. Additionally, a volume formed between adjacent first baffles20is less than a volume formed between adjacent second baffles22.

It should be understood that while, the dimensions of the resonator boxes24formed as part of the first ring30are different than the dimensions of the resonator boxes25formed as part of the second ring31that various components that form the dimensions may be altered to achieve different results, including having the same overall dimensions, or having some of the dimensions being the same, such as having the distance between two adjacent first baffles20be the same as a distance between two adjacent second baffles22, but then having the lengths of the first baffles20be different than the lengths of the second baffles22. Dimensional changes results in the acoustical frequencies compensated for by the first ring30and the second ring31being different.

Now referring to bothFIGS. 3 and 4, a plurality of holes17are formed in the first bottom portion11and a plurality of holes28are formed in the first top portion26. The distribution of the plurality of holes17and the plurality of holes28formed between the space defined by two adjacent first baffles20may vary. That is to say the number, spacing or size of the plurality of holes17may be different than the number, spacing or size of the plurality of holes28. However, it should be understood that they may be the same.

The plurality of holes19formed in the second bottom portion13and the plurality of holes29formed in the second top portion27can have a different distribution than the plurality of holes17and the plurality of holes28. Also, the distribution of the plurality of holes19and the plurality of holes29formed between the space defined by two adjacent first baffles22may vary. That is to say the number, spacing or size of the plurality of holes19may be different than the number, spacing or size of the plurality of holes29. However, it should be understood that they may be the same.

FIG. 5is a schematic diagram of the interior of the resonator ring10showing an installation of a baffle20. The installation of the baffle20shown inFIG. 4is also applicable to the installation of the baffle22. Here it is shown how the baffle20is inserted into a slot33located in the first perimeter wall12and the second perimeter wall14. Likewise, a similar slot33is found within the third perimeter wall16. The slot33permits installation of the baffles and welding to the respective walls without requiring the bottom of the baffle20to welded to the first bottom portion11. However it should be understood that baffle20can also be welded to the first bottom portion11. This permits for better disruption of circumferentially propagating acoustical waves in the first ring30. A similar set-up in the second ring31also accomplishes the same thing. In alternative embodiments, instead of being inserted into the slots33, the baffles20may be held in place through the use of labyrinth locks44, as shown inFIG. 6. Labyrinth locks44may also be located on first bottom portion11and second bottom portion13.

The usage of baffles20and baffles22allow for easier placement of resonators on the gas turbine engine5. The baffles20and the baffles22also reduce the amount of welding that may be required when using other types of resonators. Additionally the baffles20and the baffles22also reduce the amount of material needed to construct the resonators. The first ring30and the second ring31can also be adjusted to accommodate different frequencies.