초록 ▼

Variation in the available mixing plane areas in an exhaust arrangement of a gas turbine engine enables alteration and configuration for better thermal cycle performance of that engine. A shaped centre fairing is associated with an exit nozzle and a bypass duct such that channels between the fairing

Variation in the available mixing plane areas in an exhaust arrangement of a gas turbine engine enables alteration and configuration for better thermal cycle performance of that engine. A shaped centre fairing is associated with an exit nozzle and a bypass duct such that channels between the fairing, nozzle exit and duct can be adjusted to change the available areas. Such variation is achieved by relative axial displacement, typically of the exit nozzle using an appropriate mechanism.

대표청구항 ▼

1. A gas turbine engine having an exhaust arrangement, the exhaust arrangement comprising: a core exhaust having a shaped center and an exit nozzle about the shaped center arranged to define a passage therebetween, a bypass duct arranged so as to define an exhaust nozzle about the exit nozzle, the c

1. A gas turbine engine having an exhaust arrangement, the exhaust arrangement comprising: a core exhaust having a shaped center and an exit nozzle about the shaped center arranged to define a passage therebetween, a bypass duct arranged so as to define an exhaust nozzle about the exit nozzle, the core exhaust and bypass duct defining a mixing plane having a cross-section that includes: i) a first cross sectional area between the shaped center and the exit nozzle and (ii) a second cross sectional area between the exit nozzle and the bypass duct, wherein when the gas turbine engine is viewed in a cross section, the mixing plane transects at least a portion of the shaped center; and the mixing plane is; i) substantially perpendicular to a longitudinal axis of the gas turbine engine, and ii) located upstream of an exhaust nozzle exit, an axial displacement mechanism configured to extend along a longitudinal axis of the gas turbine engine to cause relative displacement of the exit nozzle relative to the shaped center and bypass duct so as to vary the ratio of the mixing plane area between the first and second cross sectional areas, so as to vary the first and second cross sectional areas. 2. The gas turbine engine as claimed in claim 1 wherein the displacement mechanism is secured to the exit nozzle to cause displacement. 3. The gas turbine engine as claimed in claim 1 wherein the first and second cross sectional areas are annular gaps. 4. The gas turbine engine as claimed in claim 1 wherein the axial displacement mechanism comprises an electrical and/or hydraulic actuator. 5. The gas turbine engine as claimed in claim 1 wherein the axial displacement mechanism is adjacent to the exit nozzle. 6. The gas turbine engine as claimed in claim 1 wherein the axial displacement mechanism includes an actuator remote from the exit nozzle and associated with the exit nozzle for displacement via a mechanical linkage. 7. The gas turbine engine as claimed in claim 1 wherein, the axial displacement mechanism comprises track slide bearings. 8. The gas turbine engine as claimed in claim 1 wherein the exhaust nozzle is variable in cross sectional area. 9. The gas turbine engine as claimed in claim 7 wherein the exhaust nozzle comprises a plurality of overlapping flat petals for varying the exhaust nozzle cross-section. 10. The gas turbine engine as claimed in claim 1 wherein the shaped center is tapered in an axial direction. 11. The gas turbine engine as claimed in claim 1 wherein the exit nozzle and shaped center are respectively shaped in order to provide up to forty percent variation in the first cross sectional area caused by the displacement mechanism. 12. The gas turbine engine as claimed in claim 1 wherein the exit nozzle and bypass duct are respectively shaped in order to provide up to forty percent variation in the second cross sectional area caused by axial displacement provided by the axial displacement mechanism. 13. The gas turbine engine as claimed in claim 1 wherein the exit nozzle, shaped center and bypass duct are respectively shaped in order to provide up to fifty percent variation in the ratio of the mixing plane area between first and second cross sectional areas as a result of axial displacement caused by the displacement mechanism. 14. The gas turbine engine as claimed in claim 1 wherein the exit nozzle is provided by a forced chuted mixer. 15. The gas turbine engine as claimed in claim 1, wherein: the exit nozzle has a lobed mixer chute at a downstream end;the shaped center is a tapering center body;the exhaust nozzle has an exit plane downstream of the bypass duct, the lobed mixer chute and center body; andthe lobed mixer chute is axially translatable between a first position and a second position, such that in the first position the second cross sectional area has a maximum flow area and the first cross sectional area has a minimum flow area and in the second position the second cross sectional area has a minimum area and the first cross sectional area has a maximum area.