Air bleed having an inertial filter in the tandem rotor of a compressor

Patent metadata

Field	Value
Publication number	US-9611862-B2
Application number	US-201013263187-A
Country	US
Kind code	B2
Filing date	Mar 31, 2010
Priority date	Apr 6, 2009
Publication date	Apr 4, 2017
Grant date	Apr 4, 2017

Abstract

The invention relates to a secondary air system for a compressor of centrifugal or mixed type including a rotor presenting an axis of rotation, said compressor being adapted to compress an oxidizer gas. The secondary air system includes an oxidizer gas bleed system arranged in the rotor.

First claim

The invention claimed is:

1. A secondary air system for a centrifugal or mixed-flow compressor having a single-piece rotor presenting an axis of rotation, said centrifugal or mixed-flow compressor being adapted to compress an oxidizer gas, the secondary air system comprising:
an oxidizer gas bleed system arranged in the single-piece rotor; and
a channeling system for channeling a bleed gas to a hot part in contact with burnt gas from a combustion chamber burning compressed gas, the hot part being part of a turbine,
wherein the channeling system includes at least one cavity internal to the single-piece rotor and a plurality of orifices made in an outer surface of the single-piece rotor, each orifice having an orifice axis extending from the outer surface of the single-piece rotor and leading into said at least one cavity internal to the single-piece rotor, the outer surface of the single-piece rotor having a plurality of main blades and a plurality of intermediate blades alternating with the plurality of main blades circumferentially on the outer surface of the single-piece rotor such that each intermediate blade on the outer surface of the single-piece rotor is between two main blades on the outer surface of the single-piece rotor in a circumferential direction, each main blade being provided with a main leading edge and each intermediate blade being provided with an intermediate leading edge which is axially downstream of the main leading edge,
wherein a trailing edge of each main blade is circumferentially aligned with a trailing edge of intermediate blade, each main blade being longer than each intermediate blade, each main blade being continuous between the respective main leading edge and the trailing edge of the respective main blade, and each intermediate blade being continuous between the respective intermediate leading edge and the trailing edge of the respective intermediate blade, and
wherein a part of one of the orifices is positioned axially between the main leading edge and the intermediate leading edge, and is positioned circumferentially between adjacent one of the intermediate blades and one of the plurality of main blades.

2. A secondary air system according to claim 1 , wherein the compressor is a compressor of a gas turbine of the type including the turbine, and
wherein the channeling system enables the bleed gas to be sent to the turbine.

3. A secondary air system according to claim 1 , wherein the single-piece rotor includes a hub, and wherein at least one of the orifices of the plurality of orifices is formed in the hub.

4. A secondary air system according to claim 1 , wherein each blade of main or intermediate type has an suction-side surface and a pressure-side surface opposite to the suction-side surface, and wherein at least the part of one of the orifices is positioned radially relative to the axis of rotation closer to the suction-side surface of the one of the main blades than to the pressure-side surface of a main blade adjacent to the one of the main blades.

5. A secondary air system according to claim 1 , wherein a flow of air flowing through each of the plurality of orifices is set by setting at least one of a first value for a first angle of inclination defined for each of the plurality of orifices as being an oriented angle formed between a first straight line that is tangential to the outer surface of the single-piece rotor and that is coplanar with the axis of rotation, and the axis of the orifice, or a second value for a second angle of inclination defined for each orifice as being the oriented angle formed between a second straight line that is tangential to the outer surface and that is orthogonal to the axis of rotation, and the axis of the orifice.

6. A secondary air system according to claim 5 , wherein the first angle of inclination in a range 0° to 90°.

7. A secondary air system according to claim 5 , wherein the second angle of inclination in a range 0° to 90°.

8. A single-piece rotor of a centrifugal or mixed-flow compressor including the secondary air system according to claim 1 .

9. A centrifugal or mixed-flow compressor including the rotor according to claim 8 .

10. A gas turbine including the centrifugal or mixed-flow compressor according to claim 9 .

11. A secondary air system according to claim 1 , wherein a top face of the one of the orifices of the plurality of orifices is positioned axially between the main leading edge and the intermediate leading edge.

Assignees

• Brillet Christophe Michel Georges Marcel
• Porodo Jerome Yves Felix Gilbert
• Tarnowski Laurent Pierre
• Turbomeca

Inventors

• Brillet Christophe Michel Georges Marcel
• Porodo Jerome Yves Felix Gilbert
• Tarnowski Laurent Pierre

Classifications

• F04D29/284 Primary

  for compressors · CPC title

• F02C7/18 Primary

  the medium being gaseous, e.g. air {(F02C7/125 takes precedence)} · CPC title

• B64D27/10

  of gas-turbine type  (jet aircraft B64D27/16) · CPC title

• F04D29/682

  by fluid extraction · CPC title

• F04D29/68

  by influencing boundary layers {(by bleeding elastic fluid F04D27/0215)} · CPC title