Work done to date on aerospace gas turbine lean burn combustion systems, and turbine tip clearance control systems, on the ANTLE and EFE demonstrator programmes has identified that there are significant challenges beyond the “conventional” scope of combustor and turbine tip clearance technologies. For example, the lean burn combustion system needs to be able to address the, sometimes conflicting, requirements of providing fuel to separate pilot and mains feeds within the burner, but without introducing regions of stagnant hot fuel with the associated risk of coking, and without complex pipe arrangements that would influence the response time of the system to demanded power change. It is essential that capability is developed in the related systems that control their operation and that these systems are fully integrated into the whole engine architecture. The objectives of this project are to increase the Technology Readiness Level of the full system capability needed to complement a lean burn combustor, and to deliver improved tip clearance control capability beyond that planned in existing programmes.