Methods and systems for cooling gas turbine engine combustors
AssigneeGeneral Electric Company
InventorsGary Lee North, Willard James Dodds
Life of this patent
Estimating the term…
Abstract
A combustor for a gas turbine includes a dome assembly that facilitates extending a useful life of the combustor in a cost-effective and reliable manner. The dome assembly includes a dome plate and a heat shield coupled to the dome plate. The dome plate includes an impingement baffle and an opening extending therethrough and sized to receive a fuel injector. The impingement baffle also includes a plurality of cooling openings in flow communication with the heat shield that direct cooling airflow for impingement cooling and film cooling of the heat shield.
Claims20
A method for supplying airflow to a gas turbine engine combustor through a dome assembly, the dome assembly including a dome plate and a heat shield, the dome plate including an impingement baffle, the heat shield coupled to the dome plate, said method comprising the steps of:
- directing compressed airflow to the impingement baffle;
- redirecting airflow towards the heat shield with the impingement baffle for impingement cooling and such that a portion of the air flow is channeled to an opposite side of the heat shield for film cooling of the heat shield;
- and
- using a seal assembly to prevent airflow from leaking between the heat shield and the dome plate, wherein the seal assembly extends radially outwardly from a radially outer edge of the heat shield to the dome plate.
A dome assembly for a gas turbine engine combustor, said dome assembly comprising:
- a dome plate comprising an impingement baffle and an opening extending therethrough and sized to receive a fuel injector;
- a heat shield extending through said dome plate opening and coupling to said dome plate, said impingement baffle configured to direct air for impingement cooling, said heat shield configured to channel a portion of the air directed from said impingement baffle for film cooling of said heat shield, said heat shield comprising a radially outer edge and a radially inner edge;
- and
- at least one seal adjacent said heat shield and extending radially outwardly from said heat shield outer edge to the dome plate.
A combustor for a gas turbine engine, said combustor comprising a dome assembly comprising a dome plate and a heat shield coupled to said dome plate, and at least one seal extending at least partially therebetween, said dome plate comprising an impingement baffle and a fuel injector opening extending therethrough, said impingement baffle configured to direct air for impingement cooling, said heat shield configured to channel a portion of the air directed from said impingement baffle for film cooling of said heat shield, said heat shield comprising a radially outer edge and a radially inner edge, said at least one seal extending radially outwardly from said heat shield outer edge to the dome plate.
Dependencies are inferred from the claim text.