Abstract: Systems and methods for controlling tip clearance in a gas turbine engine are provided. The system may include a distribution manifold positioned along the engine case for a turbine of a gas turbine engine. The distribution manifold may include a passageway for a thermal fluid, an inlet configured to direct the thermal fluid into the passageway, an inner surface extending along and facing the outer surface of the engine case, and a plurality of outlets configured to direct the thermal fluid onto the outer surface of the engine case. The thermal fluid may include bypass air. A component may add kinetic energy to the thermal fluid.

Abstract: Systems and methods for controlling tip clearance in a gas turbine engine are provided. The system may include a distribution manifold positioned along the engine case for a turbine of a gas turbine engine. The distribution manifold may include a passageway for a thermal fluid, an inlet configured to direct the thermal fluid into the passageway, an inner surface extending along and facing the outer surface of the engine case, and a plurality of outlets configured to direct the thermal fluid onto the outer surface of the engine case. The thermal fluid may include bypass air. A component may add kinetic energy to the thermal fluid.

Abstract: Systems and methods for controlling tip clearance in a gas turbine engine are provided. The system may include a distribution manifold positioned along an outer surface of an engine case of a gas turbine engine. The distribution manifold may include a plurality of outlets defined on the distribution manifold to direct a thermal fluid received by the distribution manifold onto an outer surface of the engine case of the gas turbine engine. The system may further include a variable blower configured to blow the thermal fluid into the distribution manifold at a flow rate controlled by the variable blower. The flow rate through the variable blower may be adjustable over a range of non-zero target flow rates.

Abstract: An apparatus and methods for controlling tip clearance in gas turbine engines may be provided. The apparatus and methods may include situating fins on a surface of a turbine case included in a turbine section of the gas turbine engine. The fins may act as a means for maintaining tip clearance by, for example, controlling the thermal expansion of the turbine case. The turbine case may shroud turbine blades, and the turbine blades may include tips at a radial end of the blades. During operation of the gas turbine engine, the clearance between the tips and the turbine case is desirably as small as possible while avoiding contact in order to optimize efficiency of the gas turbine engine.

Abstract: Systems and methods for controlling tip clearance in a gas turbine engine are provided. The system may include a distribution manifold positioned along an outer surface of an engine case of a gas turbine engine. The distribution manifold may include a plurality of outlets defined on the distribution manifold to direct a thermal fluid received by the distribution manifold onto an outer surface of the engine case of the gas turbine engine. The system may further include a variable blower configured to blow the thermal fluid into the distribution manifold at a flow rate controlled by the variable blower. The flow rate through the variable blower may be adjustable over a range of non-zero target flow rates.