US20180283695A1 - Combustion panel grommet - Google Patents

Combustion panel grommet Download PDF

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Publication number
US20180283695A1
US20180283695A1 US15/477,926 US201715477926A US2018283695A1 US 20180283695 A1 US20180283695 A1 US 20180283695A1 US 201715477926 A US201715477926 A US 201715477926A US 2018283695 A1 US2018283695 A1 US 2018283695A1
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United States
Prior art keywords
combustor
grommet
panel
liner
radius
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Abandoned
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US15/477,926
Inventor
San Quach
Robert M. Sonntag
Donald W. Peters
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RTX Corp
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United Technologies Corp
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Priority to US15/477,926 priority Critical patent/US20180283695A1/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SONNTAG, ROBERT M., PETERS, DONALD W., QUACH, SAN
Priority to EP18165211.6A priority patent/EP3385622A1/en
Publication of US20180283695A1 publication Critical patent/US20180283695A1/en
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: UNITED TECHNOLOGIES CORPORATION
Assigned to RAYTHEON TECHNOLOGIES CORPORATION reassignment RAYTHEON TECHNOLOGIES CORPORATION CORRECTIVE ASSIGNMENT TO CORRECT THE AND REMOVE PATENT APPLICATION NUMBER 11886281 AND ADD PATENT APPLICATION NUMBER 14846874. TO CORRECT THE RECEIVING PARTY ADDRESS PREVIOUSLY RECORDED AT REEL: 054062 FRAME: 0001. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF ADDRESS. Assignors: UNITED TECHNOLOGIES CORPORATION
Assigned to RTX CORPORATION reassignment RTX CORPORATION CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: RAYTHEON TECHNOLOGIES CORPORATION
Abandoned legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/002—Wall structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube

Definitions

  • 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.
  • the dilution hole grommets may experience high temperatures, oxidize, and contain features that reduce flow.
  • 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.
  • grommet has a frustroconical shape.
  • further embodiments could include that the second material is a ceramic matric composite.
  • further embodiments could include that the second material is a molybdenum alloy.
  • further embodiments could include that the second material is a nickel alloy.
  • further embodiments could include that the second material is a monolithic ceramic.
  • further embodiments could include that the grommet is affixed to the combustor panel.
  • further embodiments could include that the grommet is affixed to the combustor panel via a fastener.
  • further embodiments could include that the grommet is affixed to the combustor panel via a brazed joint.
  • further embodiments could include that the grommet is affixed to the combustor panel via a welded joint.
  • further embodiments could include that the grommet is affixed to the combustor panel via a threaded connection.
  • 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.
  • grommet has a frustroconical shape.
  • further embodiments could include that the second material is a ceramic matric composite.
  • further embodiments could include that the second material is a molybdenum alloy.
  • further embodiments could include that the second material is a nickel alloy.
  • 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.
  • grommet has a frustroconical shape.
  • further embodiments could include that the second material is a ceramic matric composite.
  • further embodiments could include that the second material is a molybdenum alloy.
  • FIG. 1 is a schematic, partial cross-sectional view of a turbomachine in accordance with this disclosure
  • FIG. 2 is a detail view of the combustor section for use with the turbomachine of FIG. 1 ,
  • FIG. 3A is an exploded partial isometric view of the combustor panel assembly with a grommet for use with the combustor section of FIG. 2 ;
  • FIG. 3B is a partial cross-sectional view of the combustor panel assembly with a grommet for use with the combustor section of FIG. 2 .
  • 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.
  • the gas turbine engine includes a fan section 12 , a compressor section 14 , a combustor section 16 , and a turbine section 18 disposed about a longitudinal axis A.
  • the fan section 12 drives air along a bypass flow path B that may bypass the compressor section 14 , the combustor section 16 , and the turbine section 18 .
  • the compressor section 14 draws air in along a core flow path C where air is compressed by the compressor section 14 and is provided to or communicated to the combustor section 16 .
  • the compressed air is heated by the combustor section 16 to generate a high pressure exhaust gas stream that expands through the turbine section 18 .
  • the turbine section 18 extracts energy from the high pressure exhaust gas stream to drive the fan section 12 and the compressor section 14 .
  • 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 .
  • 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 .
  • 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.
  • the combustor section 16 includes a combustor panel assembly 17 with a combustor liner 60 and a combustor panel 62 .
  • the combustor liner 60 and the combustor panel 62 can be formed from any suitable material.
  • the combustor panel 62 defines an annular shaped combustion chamber.
  • the combustor liner 60 is spaced apart from the combustor panel 62 to form an air passage between the combustor panel 62 and the combustor liner 60 to provide conditioning air.
  • the combustor panel 62 and the combustor liner 60 can include dilution holes to condition combustion air flow.
  • the combustor liner 60 includes liner dilution holes 64 and the combustor panel 62 includes panel dilution holes 66 .
  • the air exiting the compressor section 14 of the gas turbine engine 10 is typically split or bifurcated, with a portion of the compressed air being used for combustion, and a portion of the compressed air being directed to the liner dilution holes 64 and the panel dilution holes 66 for conditioning.
  • the liner dilution holes 64 and the panel dilution holes 66 can receive conditioning airflow and provide conditioning airflow to combustor components.
  • the panel dilution holes 66 receive airflow from the liner dilution holes 64 .
  • the combustor panel 62 includes an alignment stud 68 .
  • the combustor liner 60 includes an alignment hole 69 .
  • 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 .
  • the grommet 70 for use with the combustor panel assembly 17 is shown.
  • the grommet 70 includes an upper radius 72 , a lower radius 74 , an inner surface 76 and an outer surface 78 .
  • the grommet 70 can be disposed within the liner dilution hole 64 and the panel dilution hole 66 to provide a smooth continuous flow path for the conditioning air flow.
  • the use of the grommet 70 can minimize flow restrictions for conditioning airflow while providing high-temperature resistance within the combustor section 16 .
  • the grommet 70 is formed from a different material than the combustor panel 62 and the combustor liner 60 .
  • the grommet 70 is formed from a ceramic matrix composite.
  • the grommet 70 is formed from monolithic ceramics.
  • the grommet 70 is formed from molybdenum alloys.
  • the grommet 70 is formed from nickel alloys.
  • 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.
  • 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 .
  • 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.
  • 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.
  • 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 .
  • the inner surface 76 provides a continuous, uninterrupted flow path that transitions from the larger upper radius 72 to the smaller lower radius 74 .
  • 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 .
  • 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.

Abstract

A gas turbine engine and a combustor panel assembly are disclosed. The gas turbine engine 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.

Description

    BACKGROUND
  • 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.
    • BRIEF SUMMARY
  • 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.
    • BRIEF DESCRIPTION OF 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:
  • FIG. 1 is a schematic, partial cross-sectional view of a turbomachine in accordance with this disclosure;
  • FIG. 2 is a detail view of the combustor section for use with the turbomachine of FIG. 1,
  • FIG. 3A is an exploded partial isometric view of the combustor panel assembly with a grommet for use with the combustor section of FIG. 2; and
  • FIG. 3B is a partial cross-sectional view of the combustor panel assembly with a grommet for use with the combustor section of FIG. 2.
    •  DETAILED DESCRIPTION
  • 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 FIG. 1 a schematic representation of a gas turbine engine 10 is shown. The gas turbine engine includes a fan section 12, a compressor section 14, a combustor section 16, and a turbine section 18 disposed about a longitudinal axis A. The fan section 12 drives air along a bypass flow path B that may bypass the compressor section 14, the combustor section 16, and the turbine section 18. The compressor section 14 draws air in along a core flow path C where air is compressed by the compressor section 14 and is provided to or communicated to the combustor section 16. The compressed air is heated by the combustor section 16 to generate a high pressure exhaust gas stream that expands through the turbine section 18. The turbine section 18 extracts energy from the high pressure exhaust gas stream to drive the fan section 12 and the compressor section 14.
  • 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 FIG. 2, the combustor section 16 is shown. In the illustrated embodiment, the combustor section 16 includes a combustor panel assembly 17 with a combustor liner 60 and a combustor panel 62. In the illustrated embodiment, the combustor liner 60 and the combustor panel 62 can be formed from any suitable material. In the illustrated embodiment, the combustor panel 62 defines an annular shaped combustion chamber. Further, the combustor liner 60 is spaced apart from the combustor panel 62 to form an air passage between the combustor panel 62 and the combustor liner 60 to provide conditioning air. In certain embodiments, the combustor panel 62 and the combustor liner 60 can include dilution holes to condition combustion air flow.
  • As shown in FIGS. 3A and 3B, in the illustrated embodiment, the combustor liner 60 includes liner dilution holes 64 and the combustor panel 62 includes panel dilution holes 66. In the illustrated embodiment, the air exiting the compressor section 14 of the gas turbine engine 10 is typically split or bifurcated, with a portion of the compressed air being used for combustion, and a portion of the compressed air being directed to the liner dilution holes 64 and the panel dilution holes 66 for conditioning. In the illustrated embodiment, the liner dilution holes 64 and the panel dilution holes 66 can receive conditioning airflow and provide conditioning airflow to combustor components. In certain embodiments, the panel dilution holes 66 receive airflow from the liner dilution holes 64.
  • 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 FIGS. 3A and 3B, a grommet 70 for use with the combustor panel assembly 17 is shown. In the illustrated embodiment, the grommet 70 includes an upper radius 72, a lower radius 74, an inner surface 76 and an outer surface 78. In the illustrated embodiment, the grommet 70 can be disposed within the liner dilution hole 64 and the panel dilution hole 66 to provide a smooth continuous flow path for the conditioning air flow. The use of the grommet 70 can minimize flow restrictions for conditioning airflow while providing high-temperature resistance within the combustor section 16.
  • 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.

Claims (20)

What is claimed is:
1. A combustor panel assembly for use with a combustor, the combustor panel assembly comprising:
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.
2. The combustor panel assembly of claim 1, wherein the grommet has a frustroconical shape.
3. The combustor panel assembly of claim 1, wherein the second material is a ceramic matric composite.
4. The combustor panel assembly of claim 1, wherein the second material is a molybdenum alloy.
5. The combustor panel assembly of claim 1, wherein the second material is a nickel alloy.
6. The combustor panel assembly of claim 1, wherein the second material is a monolithic ceramic.
7. The combustor panel assembly of claim 1, wherein the grommet is affixed to the combustor panel.
8. The combustor panel assembly of claim 7, wherein the grommet is affixed to the combustor panel via a fastener.
9. The combustor panel assembly of claim 7, wherein the grommet is affixed to the combustor panel via a brazed joint.
10. The combustor panel assembly of claim 7, wherein the grommet is affixed to the combustor panel via a welded joint.
11. The combustor panel assembly of claim 7, wherein the grommet is affixed to the combustor panel via a threaded connection.
12. A combustor, comprising:
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.
13. The combustor of claim 12, wherein the grommet has a frustroconical shape.
14. The combustor of claim 12, wherein the second material is a ceramic matric composite.
15. The combustor of claim 12, wherein the second material is a molybdenum alloy.
16. The combustor of claim 12, wherein the second material is a nickel alloy.
17. A gas turbine engine, comprising:
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.
18. The gas turbine engine of claim 17, wherein the grommet has a frustroconical shape.
19. The gas turbine engine of claim 17, wherein the second material is a ceramic matric composite.
20. The gas turbine engine of claim 17, wherein the second material is a molybdenum alloy.
US15/477,926 2017-04-03 2017-04-03 Combustion panel grommet Abandoned US20180283695A1 (en)

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US20180306113A1 (en) * 2017-04-19 2018-10-25 United Technologies Corporation Combustor liner panel end rail matching heat transfer features
EP3702668A1 (en) * 2019-02-28 2020-09-02 Rolls-Royce plc Combustion liner and gas turbine engine comprising a combustion liner
US20220333776A1 (en) * 2021-04-20 2022-10-20 General Electric Company Gas turbine component with fluid intake hole free of angled surface transitions

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