Gas turbine engine havinga rotatable off-take passage in a compressor section

A method of operating a gas turbine engine, the gas turbine engine comprising a compressor section, the method comprising the steps of:

• operating the gas turbine engine to rotate rotational compressor components with respect to static compressor components;
• cooling one or more other components of the gas turbine engine with a compressed air bleed arrangement, the compressed air bleed arrangement taking a flow of compressed air from the compressor section along an off-take passage which opens in the compressor section in a stepped arrangement at an off-take port, the off-take passage comprising a radially outer surface that rotates with the rotational compressor components, wherein the off-take passage includes one or more vanes shaped to increase a tangential velocity of a flow of compressed air in the off-take passage in comparison to a flow of compressed air at the off-take port, and the flow of compressed air in the off-take passage is provided with higher static pressure than the flow of compressed air at the off-take port, wherein the one or more other components of the gas turbine engine includes at least one rotating component of a turbine section of the gas turbine engine and the flow of compressed air from the compressor section is delivered to the at least one rotating component with a tangential velocity that is substantially matched to a tangential velocity of the at least one rotating component.