Compressor injector apparatus and system
Cooling systems for high pressure compressor systems are provided. The cooling systems may comprise tangential on board injectors (“TOBIs”). The TOBIs may comprise one or more fluid channels configured to conduct cooling fluid flow to components of the compressor, including, for example, disk-hub portions of the compressor. In this regard, the TOBI may be configured to exhaust cooling air in a manner such that the exhausted air has a similar linear velocity of the disk-hub portion. The cooling air may also be exhausted in a manner that is substantially parallel to the disk-hub portion.
1. A compressor, comprising:
a disk-hub;
a stator portion;
a rotor portion coupled to the disk-hub, the rotor portion adjacent to and aft the stator portion;
an exit guide vane adjacent to and aft the rotor portion;
a tangential on-board injector (“TOBI”) disposed radially inward of the exit guide vane and the rotor portion, wherein the TOBI is configured to conduct a cooling flow to a section of the disk-hub adjacent the stator portion, the cooling flow isolated from a section between the rotor portion and exit guide vane by a seal.
2. The compressor of claim 1 , wherein the rotor portion is coupled to the disk-hub by a blade attachment.
3. The compressor of claim 2 , wherein the blade attachment defines a fluid conduit.
4. The compressor of claim 3 , wherein the TOM includes a first channel defined within a portion of a root of the exit guide vane and a second channel defined within a portion of a root of the rotor portion.
5. The compressor of claim 4 , wherein the first channel and the second channel are in fluid communication.
6. The compressor of claim 4 , wherein the first channel is operatively coupled to the second channel via the fluid conduit.
7. The compressor of claim 4 , wherein a first pressure (P A ) in the first channel is equivalent to a second pressure (P E ) adjacent and aft the exit guide vane.
8. The compressor of claim 7 , wherein a third pressure (P C2 ) in the second channel is equivalent to a fourth pressure (P C1 ) that is in a section between the stator portion and the rotor portion.
9. The compressor of claim 8 , wherein P A is higher than P C1 and P C2 .
10. The compressor of claim 9 , wherein a velocity of the fluid exhausting the second channel is equivalent to the linear velocity of the disk-hub.
11. A gas turbine engine, comprising:
a combustor;
a turbine in fluid communication with and configured to be driven by the combustor; and
a compressor in fluid communication with and configured to supply air to the combustor, the compressor comprising:
a disk-hub;
a rotor portion coupled to the disk-hub via a disk attachment;
an exit guide vane adjacent to and aft the rotor portion;
a tangential on-board injector (“TOBI”) disposed radially inward of the exit guide vane and the rotor portion and configured to conduct a cooling flow to a first section of the disk-hub forward of the rotor portion through a first channel and a second channel, wherein the cooling flow is exhausted from the TOBI through an outlet of the second channel at an acute angle relative to the disk-hub.
12. The gas turbine engine of claim 11 , wherein the first channel and the second channel are in fluid communication with the first section via a fluid conduit in the disk attachment, and wherein the first channel and the second channel are isolated from a second section.
13. The gas turbine engine of claim 12 , wherein the second section is defined between the rotor portion and the exit guide vane.
14. The gas turbine engine of claim 13 , wherein the second section is isolated from the first channel and the second channel by a seal.
15. A tangential on-board injector (“TOBI”) system, comprising:
a first channel defined in a root of an exit guide vane;
a second channel defined in a root of a rotor portion, the second channel in fluid communication with the first channel, the second channel configured to exhaust a cooling flow to a first section forward of rotor portion through a second channel outlet at an acute angle relative to a disk-hub.
16. The TOBI system of claim 15 , wherein a first pressure in the first channel is higher than a second pressure in the second channel.
17. The TOBI system of claim 15 , wherein the first channel and the second channel are isolated from a second section defined between the rotor portion and the exit guide vane.
18. The TOBI system of claim 15 , further comprising a third channel defined in the root of the exit guide vane, the third channel in fluid communication with a second section, wherein the second section is defined between the rotor portion and the exit guide vane.
19. The TOBI system of claim 18 , wherein the third channel is configured to conduct a cooling flow to a portion of the disk-hub associated with the second section.