A control system for a gas turbine engine comprising: a case structure; a clearance control ring mounted for movement relative to the case structure; an outer air seal mounted to the clearance control ring and facing a first engine component comprising a first rotating blade; and a control and valve assembly that receives flow from a compressor section, wherein the control and valve assembly is configured to direct flow into a first cavity positioned radially between the case structure and the outer air seal, and the control and valve assembly is configured to direct flow into a second cavity positioned downstream of the first cavity to interact with a second engine component comprising a vane, the second cavity positioned radially between the vane and the case structure, wherein the control and valve assembly is configured to control a temperature of flow supplied to the first cavity to control movement of the clearance control ring to allow the outer air seal to move in a desired direction to maintain a desired clearance between the outer air seal and the first engine component, characterised in that: the control and valve assembly includes a first control and a first valve that are configured to direct flow into the first cavity, and a second control and a second valve that are configured to direct supplemental J flow into the second cavity, such that the control and valve assembly is configured to direct the supplemental flow into the second cavity independently of directing flow into the first cavity J and the control system further includes an intermediate cavity positioned axially between the first and second cavities (68, 208), the intermediate cavity being in fluid communication with the first cavity such that flow from the first cavity is directed through the intermediate cavity and into a first inlet to the second cavity. a case structure; a clearance control ring mounted for movement relative to the case structure; an outer air seal mounted to the clearance control ring and facing a first engine component comprising a first rotating blade; and a control and valve assembly that receives flow from a compressor section, wherein the control and valve assembly is configured to direct flow into a first cavity positioned radially between the case structure and the outer air seal, and the control and valve assembly is configured to direct flow into a second cavity positioned downstream of the first cavity to interact with a second engine component comprising a vane, the second cavity positioned radially between the vane and the case structure, wherein the control and valve assembly is configured to control a temperature of flow supplied to the first cavity to control movement of the clearance control ring to allow the outer air seal to move in a desired direction to maintain a desired clearance between the outer air seal and the first engine component, characterised in that: the control and valve assembly includes a first control and a first valve that are configured to direct flow into the first cavity, and a second control and a second valve that are configured to direct supplemental J flow into the second cavity, such that the control and valve assembly is configured to direct the supplemental flow into the second cavity independently of directing flow into the first cavity J and the control system further includes an intermediate cavity positioned axially between the first and second cavities (68, 208), the intermediate cavity being in fluid communication with the first cavity such that flow from the first cavity is directed through the intermediate cavity and into a first inlet to the second cavity. the control and valve assembly includes a first control and a first valve that are configured to direct flow into the first cavity, and a second control and a second valve that are configured to direct supplemental J flow into the second cavity, such that the control and valve assembly is configured to direct the supplemental flow into the second cavity independently of directing flow into the first cavity J and the control system further includes an intermediate cavity positioned axially between the first and second cavities (68, 208), the intermediate cavity being in fluid communication with the first cavity such that flow from the first cavity is directed through the intermediate cavity and into a first inlet to the second cavity.