Patent Application
20180283695
The present disclosure relates to grommets for gas turbine engines, and more particularly to grommets for use with combustors for gas turbine engines.
Dilution holes and grommets can be utilized within combustors of gas turbine engines to condition combustion gases prior to entering the turbine for reliable operation and performance. During operation, the dilution hole grommets may experience high temperatures, oxidize, and contain features that reduce flow.
Accordingly, it is desirable to provide conditioning features that resist high temperatures and do not restrict dilution flow.
According to an embodiment, a combustor panel assembly for use with a combustor includes a combustor panel with a panel dilution hole formed therethrough, a combustor liner spaced apart from the combustor panel, wherein the combustor liner includes a liner dilution hole formed therethrough, wherein at least one of the combustor panel and the combustor liner is formed from a first material, and a grommet with a first end with a first radius, a second end with a second radius, and a continuous smooth surface between the first end and the second end, wherein the first radius is larger than the second radius, the grommet defining a flow path between the panel dilution hole and the liner dilution hole, and the grommet is formed from a second material.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the grommet has a frustroconical shape.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the second material is a ceramic matric composite.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the second material is a molybdenum alloy.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the second material is a nickel alloy.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the second material is a monolithic ceramic.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the grommet is affixed to the combustor panel.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the grommet is affixed to the combustor panel via a fastener.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the grommet is affixed to the combustor panel via a brazed joint.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the grommet is affixed to the combustor panel via a welded joint.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the grommet is affixed to the combustor panel via a threaded connection.
According to an embodiment, a combustor includes a combustor panel with a panel dilution hole formed therethrough, a combustor liner spaced apart from the combustor panel, wherein the combustor liner includes a liner dilution hole formed therethrough, wherein at least one of the combustor panel and the combustor liner is formed from a first material, and a grommet with a first end with a first radius, a second end with a second radius, and a continuous smooth surface between the first end and the second end, wherein the first radius is larger than the second radius, the grommet defining a flow path between the panel dilution hole and the liner dilution hole, and the grommet is formed from a second material.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the grommet has a frustroconical shape.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the second material is a ceramic matric composite.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the second material is a molybdenum alloy.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the second material is a nickel alloy.
According to an embodiment, a gas turbine engine includes a combustor, including a combustor panel with a panel dilution hole formed therethrough, a combustor liner spaced apart from the combustor panel, wherein the combustor liner includes a liner dilution hole formed therethrough, wherein at least one of the combustor panel and the combustor liner is formed from a first material, and a grommet with a first end with a first radius, a second end with a second radius, and a continuous smooth surface between the first end and the second end, wherein the first radius is larger than the second radius, the grommet defining a flow path between the panel dilution hole and the liner dilution hole, and the grommet is formed from a second material.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the grommet has a frustroconical shape.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the second material is a ceramic matric composite.
In addition to one or more of the features described above, or as an alternative, further embodiments could include that the second material is a molybdenum alloy.
Other aspects, features, and techniques of the embodiments will become more apparent from the following description taken in conjunction with the drawings.
The subject matter which is regarded as the present disclosure 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 present disclosure are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
Embodiments provide a grommet for use with a combustor panel assembly. The grommet provides a low restriction flow path for conditioning airflow while adding high temperature resistant material to the combustor panel assembly to allow for reliable operation and desired performance.
Referring to
The gas turbine engine 10 further includes a low-speed spool 20 and a high-speed spool 22 that are configured to rotate the fan section 12, the compressor section 14, and the turbine section 18 about the longitudinal axis A. The low-speed spool 20 may connect a fan 30 of the fan section 12 and a low-pressure compressor portion 32 of the compressor section 14 to a low-pressure turbine portion 34 of the turbine section 18. In the illustrated embodiment, the turbine section 18 can include a rotating disc assembly 35. The high-speed spool 22 may connect a high pressure compressor portion 40 of the compressor section 14 and a high pressure turbine portion 42 of the turbine section 18. The fan 30 includes a fan rotor or fan hub 50 that carries a fan blade 52. The fan blade 52 radially extends from the fan hub 50.
In the illustrated embodiment, the combustor section 16 can have operating temperatures that exceed the melting point of the materials forming the combustor section 16 components. The combustor section 16 can include dilution holes to condition combustion air.
Referring to
As shown in
In certain embodiments, the combustor panel 62 includes an alignment stud 68. Similarly, in certain embodiments, the combustor liner 60 includes an alignment hole 69. In certain embodiments, the alignment hole 69 can receive the alignment stud 68 to facilitate alignment and installation. Further, the use of the alignment hole 69 with the alignment stud 68 can allow for the liner dilution holes 64 to be aligned with the panel dilution holes 66.
Referring to
In the illustrated embodiment, the grommet 70 is formed from a different material than the combustor panel 62 and the combustor liner 60. In certain embodiments, the grommet 70 is formed from a ceramic matrix composite. In certain embodiments, the grommet 70 is formed from monolithic ceramics. In certain embodiments, the grommet 70 is formed from molybdenum alloys. In certain embodiments, the grommet 70 is formed from nickel alloys. Advantageously, the material of grommet 70 is selected to prevent melting or cracking of the grommet 70. Further, in certain embodiments, the materials of the grommet 70 are selected to have a low thermal mass to minimize stored thermal energy. Further, the material of grommet 70 can prevent the formation of oxidation.
In the illustrated embodiment, the grommet 70 is generally shaped to smoothly direct air from the outside the combustor liner 60, through the liner dilution hole 64 and through the panel dilution hole 66.
In certain embodiments, the grommet 70 is fastened to the combustor panel 62 via the panel dilution hole 66. In certain embodiments, a pressure differential keeps the grommet 70 attached to the combustor panel 62. In other embodiments, the grommet 70 is fastened to the combustor liner 60 or a combination of the combustor panel 62 and the combustor liner 60. In certain embodiments, the grommet 70 is fastened via fasteners, such as nuts, bolts, etc., brazing, welding, or a threaded connection.
In the illustrated embodiment, the geometry of the grommet 70 reduces flow restriction for conditioning flows entering the liner dilution hole 64 and the panel dilution hole 66, allowing for less work to be performed by the compressor of the engine. In the illustrated embodiment, the grommet 70 generally has a frustroconical shape, with an upper radius 72 and a lower radius 74. In the illustrated embodiment, the grommet 70 converges from the larger upper radius 72 to the smaller lower radius 74. In the illustrated embodiment, the inner surface 76 provides a continuous, uninterrupted flow path that transitions from the larger upper radius 72 to the smaller lower radius 74. In the illustrated embodiment, the outer surface 78 can interface with the combustor liner 60, the liner dilution hole 64, the combustor panel 62, and the panel dilution hole 66.
Advantageously, the materials and geometry of the grommet 70 allow for more efficient engine operation, increased durability, higher temperature operation, prevents thermal and mechanical failure, and allows for increased “time on wing” metrics.
While the present disclosure has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the present disclosure is not limited to such disclosed embodiments. Rather, the present disclosure 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 present disclosure. Additionally, while various embodiments of the present disclosure have been described, it is to be understood that aspects of the present disclosure may include only some of the described embodiments. Accordingly, the present disclosure is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.
