Tunable transition duct side seals in a gas turbine engine
View Patent ↗A system and method for tuning a gas turbine combustion system having a plurality of seals positioned between the combustion system and the turbine inlet is disclosed. The system and method provide ways of permitting a predetermined amount of compressed air to bypass the combustion system and enter the turbine so as to control emissions and dynamics of the combustion system. The seals contain a plurality of holes to meter airflow passing therethrough and are positioned such that they can be removed from the engine and modified to increase or decrease the amount of air passing therethrough.
1. A method of tuning a combustion system of a gas turbine engine comprising:
determining a portion of an airflow source to be supplied to the combustion system;
determining a size and quantity of openings for a plurality of seals based on the determined portion that will result in the portion of the airflow source being supplied to the combustion system;
placing the size and quantity of openings in the plurality of seals; and
placing the plurality of seals into the gas turbine engine in a region between adjacent double-walled transition ducts and an inlet to the turbine, wherein each of the adjacent double-walled transition ducts comprise a first sidewall and a second sidewall.
2. The method of claim 1 further comprising the step of operating the engine and determining whether the combustion system is receiving the portion of an airflow source.
3. The method of claim 2 further comprising removing the plurality of seals and altering the quantity and/or size of openings in the seal in order to adjust the portion of the airflow source to the combustion system.
4. The method of claim 1 , wherein the openings in the plurality of seals are uniform in size.
5. The method of claim 1 , wherein the openings in the plurality of seals vary in size across the seal.