Bearing compartment protection system

• US 4,709,545 A
• Filed: 01/06/1986
• Issued: 12/01/1987
• Est. Priority Date: 05/31/1983
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Brown, Wayne M., Moore, William A., Stevens, Leonard W., Barnard, Andrew A., Siwik, William S.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US06/816,693
• Time in Patent Office: 694 Days
• Field of Search: 60/39.07, 60/39.08, 60/39.75, 60/39.83, 184/6.11, 277/22, 384/139, 384/142, 384/143, 384/320, 415/111, 415/112, 415/170 R, 415/170 A, 415/175, 415/176, 415/177
• US Class Current: 60/39.08
• CPC Class Codes: F01D 11/00 Preventing or minimising internal leakage of working-fluid, e.g. between stages sealings in general F16J ; sealing arrangements for transition ducts of combustor cans F01D9/023
• CPC Class Codes: F01D 25/125 of bearings
• CPC Class Codes: F01D 25/183 Sealing means
• CPC Class Codes: F02C 7/185 Cooling means for reducing the temperature of the cooling air or gas
• CPC Class Codes: F16C 19/26 with a single row of rollers
• CPC Class Codes: F16C 2360/23 Gas turbine engines in general F02C
• CPC Class Codes: F16C 27/045 with a fluid film, e.g. squeeze film damping
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

A buffer zone adjacent to the inner diameter of carbon seals of an enclosed bearing compartment is defined by an elongated element disposed adjacent the shaft of a turbine type power plant is open ended to receive pressurized, cool air bled from the compressor to apply the cooler, higher pressure air (higher than ambient) adjacent to the seal. One embodiment contemplates feeding the buffer zone by pipes and another embodiment shrouds the bearing compartment and flows the shrouded air to the buffer zone. The buffer air with other secondary airflow cooling requirements, is utilized to cool the high pressure turbine with an overall engine performance benefit.

Claims

1. For a gas turbine engine having a compressor, and a turbine and shaft interconnecting said compressor and said turbine, a bearing compartment housing a bearing supporting said shaft interconnecting the turbine and compressor located in an environment of hot engine air, said bearing compartment surrounding said shaft and having carbon contact sealing means surrounding said shaft mounted at the ends thereof in close proximity to said shaft, wall means defining open ended chambers defining buffer zones surrounding said shaft adjacent said carbon contact sealing means for receiving buffer air, a source of air extracted from said compressor, fluid connecting means for leading buffer air from said source to a point external of said engine into each of said buffer zones at a point in direct communication with the open end of a chamber so that a portion of said buffer air flows out of each of said open ends of said chambers and into said turbine for cooling purposes, said buffer air being at a pressure higher than the pressure of said hot air in said environment so that a small portion of the buffer air leaks through said carbon seal, and the remaining portion is directed toward said turbine heat exchanger means intermediate said source and said buffer zones for coolign the buffer air prior to being admitted into said buffer azones and the buffer air normally flowing out of said open end flows into said bearing compartment in the event of a failure of said carbon contact sealing means.

2. For a gas turbine engine as in claim 1 wherein said fluid connecting means includes at least one pipe internall of said engine receiving buffer air from said heat exchanger connecting each of said chambers at a point intermediate the ends thereof.

3. For a gas turbine engine as in claim 2 wherein each of said pipes are concentrically mounted in an outer pipe radially spaced therefrom providing a dead air space for insulating the buffer air in each of said pipes.

4. For a gas turbine engine as in claim 1 wherein said fluid connecting means includes a sheath surrounding said bearing compartment and spaced therefrom for defining an annular passageway for receiving buffer air, said buffer air first scrubbing said bearing compartment prior to being admitted into said open ended chamber.

5. For a gas turbine engine as in claim 4 including openings in said wall means of said open ended chambers interconnecting said annular passageway and said open ended chambers at a point intermediate the ends of said open ended chambers.

6. For a gas turbine egine as in claim 5 including a second sheat surrounding the other sheath but spaced therefrom defining a dead-ended annular chamber for insulating the buffer air in said other sheath.