GAS TURBINE ENGINE COMBUSTOR
First Claim
1. A combustor for a gas turbine engine, comprising:
- a combustor shell;
a heat shield mounted to the combustor shell spaced-apart from the combustor shell to define an air gap therebetween;
a core dilution passageway extending through the combustor shell and the heat shield;
a sub-chamber disposed within the air gap in fluid communication with the core dilution passageway, the sub-chamber being separated from a remainder of the air gap by at least one intermediate rail projecting across the air gap and forming an outer boundary of a peripheral area of the core dilution passageway; and
impingement holes formed through the combustor shell and in fluid communication with the sub-chamber.
1 Assignment
0 Petitions
Accused Products
Abstract
A combustor for a gas turbine engine including a combustor shell, a heat shield mounted to the combustor shell spaced-apart from the combustor shell to define an air gap therebetween, a core dilution passageway extending through the combustor shell and the heat shield, and a sub-chamber disposed within the air gap in fluid communication with the core dilution passageway. The sub-chamber is separated from a remainder of the air gap by at least one intermediate rail projecting across the air gap and forming an outer boundary of a peripheral area of the core dilution passageway. Impingement holes are formed through the combustor shell and in fluid communication with the sub-chamber. A method of cooling an area surrounding a dilution hole in a combustor is also presented.
-
Citations
20 Claims
-
1. A combustor for a gas turbine engine, comprising:
-
a combustor shell; a heat shield mounted to the combustor shell spaced-apart from the combustor shell to define an air gap therebetween; a core dilution passageway extending through the combustor shell and the heat shield; a sub-chamber disposed within the air gap in fluid communication with the core dilution passageway, the sub-chamber being separated from a remainder of the air gap by at least one intermediate rail projecting across the air gap and forming an outer boundary of a peripheral area of the core dilution passageway; and impingement holes formed through the combustor shell and in fluid communication with the sub-chamber. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9, 10, 11, 12, 13, 14, 15)
-
-
16. A gas turbine engine, comprising:
a combustor including; a combustor shell; a heat shield mounted to the combustor shell spaced-apart from the combustor shell to define an air gap therebetween, the combustor shell including impingement holes configured to provide impingement jets onto the heat shield; a first dilution hole defined in the combustor shell in registry with a corresponding second dilution hole defined in the heat shield, the first dilution hole and the second dilution hole defining a core dilution passageway; and the second dilution hole having a boss at its rim, spaced apart from the combustor shell, such that the gap fluidly communicates with the core dilution passageway. - View Dependent Claims (17)
-
18. A method of cooling an area surrounding a dilution hole in a combustor, the combustor having a heat shield spaced-apartedly mounted to a combustor shell to define an air gap, the method comprising:
-
flowing a peripheral dilution flow through the combustor shell to a sub-chamber that is pressurised in relation to a remainder of the air gap and around a boss formed at a rim of the dilution hole, the sub-chamber extending within a peripheral area of the dilution hole, the peripheral dilution flow accounting for at least 5% of a total dilution flow; and merging the peripheral dilution flow with a core dilution flow of the dilution hole to form the total dilution flow. - View Dependent Claims (19, 20)
-
Specification