The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within an end cover, a common fuel tube extending through the end cover and in communication with the micro-mixer fuel nozzles, a linear actuator to maneuver the common fuel tube and the micro-mixer fuel nozzles, and a sealing support structure positioned between the end cover and the common fuel tube.
STATEMENT REGARDING FEDERALLY SPONSORED RESEARCH OR DEVELOPMENT
 This invention was made with government support under Contract No. DE-FC26-05NT42643 awarded by the U.S. Department of Energy. The Government has certain rights in this invention.