Combustor having a beveled grommet
A combustor includes a shell that at least partially defines a combustion chamber and a grommet mounted in the shell. The grommet has a body that defines a passage through the grommet that is operable to communicate air from outside the combustion chamber into the combustion chamber. The body carries a first surface, an opposite, second surface and a third surface that defines the passage and joins the first surface and the second surface. The third surface includes a bevel surface with respect to at least one of the first surface and the second surface.
1. A combustor comprising:
a shell at least partially defining a combustion chamber, the shell including heat shield panels and a peripheral wall;
plurality of quench ports for introducing air from outside the peripheral wall into the combustion chamber; and
a grommet mounted in the shell within the plurality of quench ports, the grommet having a body defining a passage through the grommet that is operable to communicate air from outside the combustion chamber into the combustion chamber, the body carrying a first surface, an opposite, second surface and a third surface defining the passage and joining the first surface and the second surface, the third surface including a bevel surface with respect to at least one of the first surface and the second surface, and the grommet includes a circumferential flange that is arranged between the heat shield panels and the peripheral wall;
wherein the grommet is flush with at least the heat shield panels, and wherein the grommet is also flush with the peripheral wall.
2. The combustor as recited in claim 1 , wherein the bevel surface is angled at about 35°-55° with regard to a central axis of the passage.
3. The combustor as recited in claim 2 , wherein the bevel surface is angled at about 45° with regard to a central axis of the passage.
4. The combustor as recited in claim 1 , wherein the grommet defines an axial thickness (t) with regard to a central axis of the passage and the bevel surface defines an axial length component (L 1 ) such that a ratio L 1 /t is 0.1-0.4.
5. The combustor as recited in claim 1 , wherein the passage has a diameter (D) and the bevel surface defines a radial length component (L 2 ) such that a ratio L 2 /D is about 0.05-0.09.
6. The combustor as recited in claim 1 , wherein the grommet defines an axial thickness (t) with regard to a central axis of the passage and the bevel surface defines an axial length component (L 1 ) and a radial length component L 2 such that a ratio L 1 /t is about 0.1-0.4 and a ratio L 2 /D is about 0.05-0.09.
7. The combustor as recited in claim 1 , wherein the grommet is a separate and distinct piece from the shell.
8. A turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor,
the combustor including:
a shell at least partially defining a combustion chamber, the shell including heat shield panels and a peripheral wall,
plurality of quench ports for introducing air from outside the peripheral wall into the combustion chamber; and
a grommet mounted in the shell within the plurality of quench ports, the grommet having a body defining a passage through the grommet that is operable to communicate air from outside the combustion chamber into the combustion chamber, the body carrying a first surface, an opposite, second surface and a third surface defining the passage and joining the first surface and the second surface, the third surface including a bevel surface with respect to at least one of the first surface and the second surface, and the grommet includes a circumferential flange that is arranged between the heat shield panels and the peripheral wall;
wherein the grommet is flush with at least the heat shield panels, and wherein the grommet is also flush with the peripheral wall.
9. The turbine engine as recited in claim 8 , wherein the bevel surface is angled at 35°-55° with regard to a central axis of the passage.
10. The turbine engine as recited in claim 8 , wherein the grommet defines an axial thickness (t) with regard to a central axis of the opening and the bevel surface defines an axial length component (L 1 ) such that a ratio L 1 /t is 0.1-0.4, and the passage defines a diameter (D) and the bevel surface defines a radial length component (L 2 ) such that a ratio L 2 /D is 0.05-0.09.
11. The turbine engine as recited in claim 8 , wherein the bevel surface extends over an axial length component L 1 with regard to a central axis of the passage and over a radial length component L 2 that is equal to L 1 .
12. A combustor comprising:
a shell at least partially defining a combustion chamber, the shell including heat shield panels and a peripheral wall;
plurality of quench ports for introducing air from outside the peripheral wall into the combustion chamber; and
a grommet mounted in the shell within the plurality of quench ports, the grommet having a body defining a passage through the grommet that is operable to communicate air from outside the combustion chamber into the combustion chamber, the body carrying a first surface, an opposite, second surface and a third surface defining the passage and joining the first surface and the second surface, the third surface including a bevel surface with respect to at least one of the first surface and the second surface, and the grommet is flush with at least the heat shield panels, and wherein the grommet is also flush with the peripheral wall.