Temperature controlling apparatus
An apparatus for controlling the temperature of a component, which is situated in use in a gas stream, provides a nozzle to create a jet of air at an angle to the gas stream, the jet being directed into the region of the stagnation point of the component so as to control the temperature of the component. The invention is particularly suited to preventing or reducing the formation of ice on vanes of gas turbine engines, but may also be applied to other components, and may equally be used in situations where a component is to be cooled rather than heated.
1. An apparatus for preventing or diminishing formation of ice on a component, the component situated in use in a duct in which flows a gas stream, whereby a stagnation point is created in the region of an upstream portion of the component, the apparatus comprising:
a nozzle located in a wall of the duct and at an axial position corresponding to the axial position of the stagnation point, said nozzle positioned and connected to introduce into the gas stream a jet of air hotter than the gas stream and directed generally parallel to a surface of the component and into the region of the stagnation point.
2. An apparatus as claimed in claim 1 , in which the component is a component of a gas turbine engine.
3. An apparatus as claimed in claim 1 , in which the component is a vane or strut.
4. An apparatus as claimed in claim 3 , in which the component is a variable vane.
5. An apparatus as claimed in claim 4 , in which the variable vane comprises a mounting member, the mounting member forming a part of the duct wall, and in which the nozzle is located in the mounting member.
6. An apparatus as claimed in claim 2 , in which the jet of air is fed from a bleed offtake or another gas turbine engine or an APU or a ground cart.
7. An apparatus as claimed in claim 1 , and comprising a plurality of nozzles associated with the component, each nozzle creating a jet of air, in which the jets are directed at different angles.
8. An apparatus as claimed in claim 1 , and comprising a plurality of nozzles associated with the component, each nozzle creating a jet of air, in which the jets are directed at different regions of the component.
9. A gas turbine engine comprising, in axial flow series:
an air intake;
a propulsive fan;
an intermediate pressure compressor;
a high pressure compressor;
a combustor;
a turbine including a high pressure turbine, an intermediate pressure turbine, a low pressure turbine, and an exhaust nozzle,
said turbines including a plurality of components, with at least one component situated in use in a duct in which flows a gas stream, whereby a stagnation point is created in the region of an upstream portion of the component, and
said turbines including at least one apparatus for controlling the temperature of said at least one component, said apparatus including a nozzle located in a wall of the duct and at an axial position corresponding to the axial position of the stagnation point, said nozzle positioned and connected to introduce into the gas stream a jet of air hotter than the gas stream and directed generally parallel to a surface of the component and into the region of the stagnation point.