Abstract: Cooling jets 1 are provided with a longitudinal aspect 2 greater than width 3. Thus, the coolant flow through the jet 1 is less susceptible to deflection by lateral or cross flows presented to that coolant flow such that cooling by impingement of the coolant flow upon a surface 7 to be cooled is improved. Typically, a plurality of jets 1 are provided in a housing wall 8. These jets 1 will be arranged in an appropriate pattern to achieve cooling by flow impingement upon the surface 7 to be cooled. Possibly, a plurality of jets 1 in an appropriate pattern may be arranged upstream of conventional circular coolant jets in order to provide some protection for those circular coolant jets from lateral or cross flow.

Abstract: Efficient cooling of a stage of gas turbine engine turbine blades (36) is achieved by first reducing the pressure of the cooling air after it has been bled from the annulus of the compressor (12) by passing it through a diffuser (30), to a pressure magnitude lower than is required at entry to the turbine blades, then re-pressurising the bled air up to the required entry pressure, by passing it through a radial compressor defined by a cowl (44) positioned in close spaced, co- rotational relationship with the downstream face of the associated turbine disk (34).

Abstract: Rotary apparatus (17) for a gas turbine engine (10) comprises a rotor assembly (63) and first and second stator assemblies (55, 59) mounted coaxially with respect to each other. The first stator assembly (55) is upstream of the second stator assembly (59), and the second stator assembly (59) is upstream of the rotor assembly (63). The rotor assembly (63) comprises an annular array (64) of rotor blades (66), and each stator assembly (55, 59) comprises an annular array (56, 60) of stator vanes (58, 62). Each vane (58, 62) has a leading edge and a trailing edge. The stator assemblies (55, 59) are circumferentially translatable relative to each other between a first condition in which each of the vanes (62) of the second stator assembly (59) is substantially aerodynamically aligned with a respective one of the vanes (58) of the first stator assembly (55), and a second condition in which the vanes (58, 62) of the first and second stator assemblies (55, 59) are out of aerodynamic alignment with each other.

Abstract: Cooling jets 1 are provided with a longitudinal aspect 2 greater than width 3. Thus, the coolant flow through the jet 1 is less susceptible to deflection by lateral or cross flows presented to that coolant flow such that cooling by impingement of the coolant flow upon a surface 7 to be cooled is improved. Typically, a plurality of jets 1 are provided in a housing wall 8. These jets 1 will be arranged in an appropriate pattern to achieve cooling by flow impingement upon the surface 7 to be cooled. Possibly, a plurality of jets 1 in an appropriate pattern may be arranged upstream of conventional circular coolant jets in order to provide some protection for those circular coolant jets from lateral or cross flow.