Balancing a pressure drop across ring seals in gas turbine engines

• US 6,132,168 A
• Filed: 12/23/1998
• Issued: 10/17/2000
• Est. Priority Date: 12/23/1998
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Craig, Colin D., Kovaleski, Donald J., Kovaleski, Stanley K.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): NGUYEN, NINH H
• Application Number:
  US09/220,467
• Time in Patent Office: 664 Days
• Field of Search: 415/111, 415/113, 415/112, 415/104, 415/107, 415/174.5, 415/168.2, 415/168.4, 277/365, 277/366, 277/399, 277/422, 277/928
• US Class Current: 415/113
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 11/003 by packing rings; Mechanical seals
• CPC Class Codes: F16J 15/443 provided with discharge channels

Abstract

A gas turbine engine includes a plurality of seal stages minimizing leakage of high pressure air from a high pressure cavity into a low pressure cavity. The plurality of seal stages includes an upstream seal stage, substantially adjacent to the high pressure cavity, and a downstream seal stage, substantially adjacent to the low pressure cavity. Each seal stage includes a seal plate and at least one seal. The downstream seal plate includes a plurality of bleeding holes for metering higher pressure air into the low pressure cavity, thereby balancing a pressure drop between the seal stages. Substantial equalization of the pressure drop among the seal stages reduces wear of the downstream seal and therefore, increases useful life an effectiveness thereof.

Claims

1. A seal plate for retaining a seal in a predetermined location in a gas turbine engine, said seal plate comprising:

a seal plate body shaped to cooperate with said seal, said seal plate body having a plurality of bleeding holes to allow air from a higher-pressure air area to pass therethrough to a lower-pressure air area.

2. The seal plate according to claim 1 wherein said bleeding holes of said seal plate are substantially equally spaced around circumference of said seal plate.

3. The seal plate according to claim 1 wherein said bleeding holes are angled with respect to a center axis of said gas turbine engine to prevent oil and debris from entering said bleeding holes.

4. A gas turbine engine having a first cavity with a higher pressure air and a second cavity with a lower pressure air, said gas turbine engine comprising:

a first seal stage disposed substantially adjacent to said first cavity for minimizing leakage of higher pressure air from said first cavity, said first seal stage including at least one first seal and a first seal plate retaining said first seal in a first predetermined location; and

a second seal stage disposed substantially adjacent to and downstream from said first seal stage for minimizing leakage of higher pressure air from said first seal stage, said second seal stage comprising at least one second seal and a second seal plate retaining said second seal in a second predetermined location, said second seal plate having a second seal plate plurality of bleeding holes for allowing a portion of higher pressure air to pass therethrough.

5. The gas turbine engine according to claim 4 further comprising:

a third seal stage disposed substantially adjacent to and downstream from said second seal stage, said third seal stage having at least one third seal and at least one third seal plate, said third seal plate having a third seal plate plurality of bleeding holes for allowing higher pressure air to escape from said second seal stage and to seep into said second cavity.

6. The gas turbine engine according to claim 5 wherein said third seal stage includes two third seals separated by a spring.

7. The gas turbine engine according to claim 5 wherein said third seal stage includes a single third seal.

8. The gas turbine engine according to claim 4 wherein each said seal stage includes one seal.

9. The gas turbine engine according to claim 4 wherein each said seal stage includes two seals separated by a spring.

10. The gas turbine engine according to claim 4 wherein said bleeding holes of said second seal plate are substantially equally spaced around circumference of said second seal plate.

11. The gas turbine engine according to claim 4 wherein said bleeding holes are angled with respect to a center axis to prevent oil and debris from entering said bleeding holes.

12. A gas turbine engine having a low compressor, a high compressor, a combustor, a high turbine and a low turbine situated along a longitudinal axis, said high compressor and said high turbine including a plurality of rows of rotating blades attached to a high rotor and said low compressor and said low turbine including a plurality of rows of rotating blades attached to a low rotor, said high rotor being disposed radially outward of said low rotor, said gas turbine engine comprising:

a plurality of seal stages disposed between said low rotor and said high rotor to minimize leakage of higher pressure air from a first cavity with higher pressure air downstream to a second cavity with lower pressure air, said plurality of seal stages having a downstream seal stage substantially adjacent to said second cavity and an upstream seal stage substantially adjacent to said first cavity, said downstream seal stage having a downstream seal plate having a plurality of downstream bleeding holes formed therein to substantially balance pressure drop between said seal stages.

13. The gas turbine engine according to claim 12 wherein said plurality of seal stages further includes a midstream seal stage disposed between said downstream seal stage and said upstream seal stage, said midstream seal stage having a midstream seal plate having a plurality of midstream bleeding holes formed therein to further balance pressure drop between said plurality of seal stages.

14. A gas turbine engine having a compressor, a combustor, and a turbine situated along a longitudinal axis, said compressor and said turbine including a plurality of rows of rotating blades attached to a rotor, said gas turbine engine comprising:

a plurality of seal stages disposed about said rotor to minimize leakage of higher pressure air from a first cavity with higher pressure air downstream to a second cavity with lower pressure air, said plurality of seal stages having a downstream seal stage substantially adjacent to said second cavity and an upstream seal stage substantially adjacent to said first cavity, said downstream seal stage having a downstream seal plate having a plurality of downstream bleeding holes formed therein for metering a portion of higher pressure air therethrough to substantially balance pressure drop between said plurality of seal stages.