Anti-ice splitter nose

Patent metadata

Field	Value
Publication number	US-9777632-B2
Application number	US-201314889752-A
Country	US
Kind code	B2
Filing date	May 7, 2013
Priority date	May 7, 2013
Publication date	Oct 3, 2017
Grant date	Oct 3, 2017

Abstract

Splitter apparatus for gas turbine engines are disclosed. An example splitter apparatus may include a splitter including an annular outer wall substantially defining a convex leading edge; an annular splitter support positioned radially within the outer and including a forward end disposed substantially against a splitter inner; and an annular first bulkhead spanning between the outer wall and the splitter support. The outer wall, the splitter support, and the first bulkhead may define a generally annular splitter plenum. The forward end of the splitter support may include spaced apart, radially oriented metering slots. The outer wall may include an inner portion disposed radially inward from the splitter inner surface extending aft and including spaced-apart exit slots. The splitter plenum, the metering slots, and the exit slots may conduct airflow from the plenum, through the metering slots against the splitter inner surface, and through the exit slots.

First claim

What is claimed is:

1. A splitter apparatus for a gas turbine engine, comprising:
a splitter including a generally annular outer wall substantially defining a convex leading edge at a forward end of the outer wall;
a generally annular splitter support positioned radially within the outer wall, the splitter support comprising a forward end disposed substantially against a splitter inner surface of the outer wall; and
a generally annular first bulkhead spanning between the outer wall and the splitter support, wherein the outer wall, the splitter support, and the first bulkhead collectively substantially define a generally annular splitter plenum;
wherein the forward end of the splitter support comprises a plurality of circumferentially spaced apart, generally radially oriented metering slots therein;
wherein the outer wall comprises an inner portion disposed generally radially inward from the splitter inner surface and extending generally aft, the inner portion comprising a plurality of spaced-apart exit slots; and
wherein the splitter plenum, the metering slots, and the exit slots are arranged to conduct airflow from the plenum, through the metering slots substantially against the splitter inner surface, and through the exit slots.

2. The apparatus of claim 1 , wherein the forward edge of the splitter support is disposed substantially in contact with, but is not attached to, the splitter inner surface.

3. The apparatus of claim 1 , further comprising a generally radially oriented vane disposed radially inward of the splitter, the vane being mounted to an outer band comprising a forwardly extending forward rail positioned radially between the splitter support and the inner portion of the outer wall.

4. The apparatus of claim 3 , further comprising a generally annular, resilient seal disposed between the outer band and the splitter support.

5. The apparatus of claim 1 , wherein a number of metering slots is about twice a number of exit slots.

6. The apparatus of claim 1 , wherein a number of metering slots is about three times a number of exit slots.

7. The apparatus of claim 1 , wherein a number of metering slots associated with an individual exit slot varies circumferentially.

8. The apparatus of claim 1 , wherein the plurality of metering slots comprises metering slots of a first width and a second width different than the first width.

9. The apparatus of claim 1 , wherein a spacing between adjacent ones of the metering slots varies circumferentially around the splitter support.

10. The apparatus of claim 1 , wherein a spacing between adjacent ones of the metering slots is substantially constant circumferentially around the splitter support.

11. A gas turbine engine, comprising:
a rotatable fan;
a rotatable booster disposed aft of the fan;
a turbomachinery core disposed aft of the booster and operable to generate a flow of pressurized combustion gases;
a generally annular core nacelle disposed radially around the booster and the turbomachinery core;
a low-pressure turbine disposed aft of the turbomachinery core and mechanically coupled to the booster and the fan;
a radial array of airfoils disposed forward of the booster and substantially circumscribed by a generally annular outer band;
a splitter disposed at a forward end of the core nacelle and surrounding the outer band, the splitter including:
a generally annular outer wall substantially defining a convex-curved leading edge at a forward end of the outer wall;
a generally annular splitter support positioned radially within the outer wall, the splitter support comprising a forward end disposed in contact with a splitter inner surface of the outer wall; and
a generally annular first bulkhead spanning between the outer wall and the splitter support, wherein the outer wall, the splitter support, and the first bulkhead substantially define a generally annular splitter plenum;
wherein the forward end of the splitter support comprises a plurality of circumferentially spaced apart, generally radially oriented metering slots therein;
wherein the outer wall comprises an inner portion disposed generally radially inward from the splitter inner surface and extending generally aft, the inner portion comprising a plurality of spaced-apart exit slots; and
wherein the splitter plenum, the metering slots, and the exit slots are arranged to conduct airflow from the plenum, through the metering slots substantially against the splitter inner surface, and through the exit slots.

12. The gas turbine engine of claim 11 , wherein the outer band comprises a forwardly extending forward rail disposed radially between the splitter support and the inner portion of the outer wall.

13. The gas turbine engine of claim 12 , further comprising a seal disposed between the outer band and the splitter support, the seal substantially preventing airflow between the outer band and the splitter support.

14. The gas turbine engine of claim 11 ,
wherein the outer wall comprises a radially inwardly extending, generally annular aft bulkhead;
wherein the outer band comprises a radially outwardly extending, generally annular flange; and
wherein the flange of the outer band is coupled to the aft bulkhead.

15. The gas turbine engine of claim 11 , wherein individual ones of the plurality of exit slots are generally semi-circular.

16. The gas turbine engine of claim 11 , wherein a spacing between adjacent ones of the exit slots varies circumferentially around the outer wall.

17. The gas turbine engine of claim 11 , wherein an individual one of the exit slots are arranged to receive airflow from two or more of the metering slots.

18. The gas turbine engine of claim 11 , wherein an individual one of the exit slots is arranged to receive airflow from three or more of the metering slots.

19. The gas turbine engine of claim 11 , wherein the plurality of metering slots comprises metering slots of a first width and a second width different than the first width.

20. The gas turbine engine of claim 11 , wherein a spacing between adjacent ones of the metering slots varies circumferentially around the splitter support.

Assignees

• Gen Electric

Inventors

• Prather Randall Maurice
• Cunningham Neil Fraser
• Jih Junhaur
• Krammer Erich Alois
• Subramanian Sesha

Classifications

• F01D25/02

  De-icing means for engines having icing phenomena · CPC title

• Y02T50/672

  Cross-Sectional Technologies · mapped topic

• F05D2260/201

  by impingement of a fluid · CPC title

• F02C7/047 Primary

  Heating to prevent icing · CPC title

• Y02T50/675

  Cross-Sectional Technologies · mapped topic