Bleed valve arrangement
Problems can arise with regard to noise created by bleed valve arrangements in gas turbine engines. It is known to utilize pressure differential inducing elements such as pepper pots and perforated surfaces in order to attenuate noise from bleed valves. However, these arrangements tend to have a portion which expands such that the exit aperture into a bypass duct wall can significantly affect mechanical strength and operational performance. By providing internally created pepper pots or other pressure differential inducing elements within a path of an arrangement and a constriction to an exit noise attenuation is still achieved but with less detrimental effect with regard to bypass duct wall strength and aerodynamic losses altering operational performance.
1. A gas turbine engine comprising:
a bypass duct wall;
a core engine casing; and
a bleed valve arrangement, wherein:
the bleed valve arrangement extends from an inlet in the core engine casing to an outlet in the bypass duct wall,
the bleed valve arrangement has a plurality of perforated plates arranged in series through which a bleed flow passes,
the bleed valve arrangement defines an exit duct well that is defined by the last perforated plate at a downstream end in which the bleed flow passes of the plurality of perforated plates and the outlet, and
the exit duct well is constricted by a constriction between the last perforated plate and the outlet.
2. The gas turbine engine as claimed in claim 1 wherein a perforated surface of the perforated plates is curved to provide vibration resistance.
3. The gas turbine engine as claimed in claim 1 wherein perforations in the perforated plates are angled to direct flow.
4. The gas turbine engine as claimed in claim 1 wherein the bleed valve arrangement includes a valve.
5. The gas turbine engine as claimed in claim 1 wherein the bleed valve arrangement includes a baffle plate.
6. The gas turbine engine as claimed in claim 1 wherein a path of the bleed valve arrangement is between a bypass duct and a compressor stage of the gas turbine engine.
7. The gas turbine engine as claimed in claim 1 wherein a path of the bleed valve arrangement is angled and/or a curve.
8. The gas turbine engine as claimed in claim 1 wherein there is a ratio between a cross sectional area C of a portion of a path of the bleed valve arrangement relative to the constriction D to provide a desired level of sudden expansion for fluid flow after the outlet.
9. The gas turbine engine as claimed in claim 8 wherein the portion of the path has the greatest cross sectional area of the path.
10. The gas turbine engine as claimed in claim 8 wherein the ratio is greater than 1.
11. The gas turbine engine as claimed in claim 8 wherein the ratio is in the range 1 to 10.
12. The gas turbine engine as claimed in claim 8 wherein the ratio is substantially 3.
13. The gas turbine engine as claimed in claim 1 wherein the constriction comprises an aperture to form the outlet in the bypass duct wall.
14. The gas turbine engine as claimed in claim 1 wherein the outlet includes vanes or vents to direct and/or limit fluid flow through the outlet.