Lubricating system for gas turbine engines

• US 4,511,016 A
• Filed: 11/07/1983
• Issued: 04/16/1985
• Est. Priority Date: 11/16/1982
• Status: Expired due to Fees

• Current Assignee: MTU Motoren- und Turbinen-Union Muenchen GmbH (MTU)
• Original Assignee: MTU Motoren- und Turbinen-Union Muenchen GmbH (MTU)
• Inventors: Doell, Hermann
• Primary Examiner(s): NOT, DEFINED
• Assistant Examiner(s): Griffiths, John E.
• Application Number:
  US06/549,413
• Time in Patent Office: 526 Days
• Field of Search: 184/6, 184/6.2, 184/6.3, 184/6.4, 184/6.11, 184/6.21, 184/6.22, 184/6.23, 184/6.24, 184/6.28, 184/7.1, 184/26, 184/104 R, 60/39.08, 137/43, 137/45, 244/135 R, 123/196 R, 123/196 S
• US Class Current: 184/6.11
• CPC Class Codes: F01D 25/20 using lubrication pumps
• CPC Class Codes: F16N 7/40 in a closed circulation system

Abstract

Components, such as bearings, of gas turbine engines especially for aircraft are lubricated by a lubricant supply system including a main lubricant circulating circuit and an auxiliary lubricant circulating circuit for assuring a sufficient lubricant supply to the lubricating chamber or chambers under all operating conditions including those causing extremely rapid and locally differing displacements of the lubricant fluid in its supply tank. The main lubricant circulating circuit with its pumps, lubricating chamber or chambers, cooler, air separator and accumulator is operatively connected to the component being lubricated and is effective during normal and critical flight conditions. The auxiliary circulatory circuit with its lubricant supply tank and its pump is operatively connected to the main circulatory circuit for supplying lubricant into the main circuit. The auxiliary circulatory circuit is effective during the engine start-up and for replenishing lubricant into the main circuit during normal flight conditions.

Claims

1. A lubricating system for gas turbine engines, comprising a lubricant circulating circuit including lubricating chamber means (2), lubricant pressure pump means (1) and a main supply conduit means (14) operatively connecting said pressure pump means to a pressure input of said lubricating chamber means for lubricating an engine component in said lubricating chamber means, suction pump means (4) operatively connected to a suction output of said lubricating chamber means (2), lubricant air separator means (6) vented to the atmosphere, conduit means (2'"'"') operatively connecting said lubricant air separator means (6) to said suction pump means (4), return conduit means (11) operatively connecting said lubricant air separator means (6) back to said pressure pump means (1), and lubricant storage accumulator means (7) operatively connected to said return conduit means (11), said system comprising a further pressure pump means (9), lubricant supply container means (8), and auxiliary conduit means (12) operatively connecting said further pressure pump means (9) to said main supply conduit means (14) of said lubricant circulating circuit for replenishing lubricant from said supply container means (8) only during engine starting and during engine operation under normal flight conditions, said main supply conduit means (14) comprising first valve means (15), said return conduit means (11) comprising second valve means (13, 21), and said auxiliary conduit means (12) comprising third valve means (17), said first, second and third valve means being responsive to variable oil pressures occurring in said respective conduit means for assuring a lubrication in said lubricating chamber means (2) independently of gravity, especially zero gravity, influences under critical flight conditions.

2. The system of claim 1, wherein said lubricating chamber means (2) comprise venting conduit means (10) operatively connecting said lubricating chamber means to said lubricant air separator means (6) for venting said lubricating chamber means to the atmosphere through said lubricant air separator means (6).

3. The system of claim 1, wherein said auxiliary conduit means comprise an auxiliary pressure conduit (12), said third valve means comprises a non-return valve (17) in said auxiliary pressure conduit, and a return auxiliary conduit (16), said auxiliary pressure conduit (12) connecting a pressure outlet of said further pressure pump (9) through said non-return valve (17) to an inlet of said first mentioned pressure pump (1), and said second valve means include a further non-return valve (13) in said return conduit means (11), said further non-return valve (13) being located directly downstream of a point where said auxiliary pressure conduit (12) is connected to said inlet of said first mentioned pressure pump (1).

4. The system of claim 1, wherein said first valve means in said main supply conduit means (14) between said first mentioned pressure pump means (1) and said lubricating chamber means (2) comprises a two-way valve (15) in said main supply conduit means (14), said auxiliary conduit means including an auxiliary return conduit (16) connecting said two-way valve (15) to said lubricant supply container means (8) for returning excess lubricant into said lubricant supply container means (8), said two-way valve (15) closing said auxiliary return conduit (16) for assuring a flow of lubricant through said main supply conduit means (14) under said critical flight conditions.

5. The system of claim 1, wherein said lubricant supply container means (8) comprise a venting conduit (18) operatively connecting said lubricant supply container means to said lubricant air separator means (6) for venting said lubricant supply container means through said lubricant air separator means.

6. The system of claim 1, wherein said conduit means (2'"'"') comprise lubricant cooling means (5) operatively connected between said suction pump means (4) and said lubricant air separator means.

7. The system of claim 1, wherein said lubricant air separator means comprises a lubricant outlet port operatively connected to an inlet port of said lubricant pressure pump means (1) by said return conduit means.

8. The system of claim 7, wherein said valve means in said return conduit means (11) comprise a non-return valve (21) for connecting and disconnecting said lubricant storage accumulator means (7) to said return conduit means (11) between said inlet port of said lubricant pressure pump means (1) and said lubricant outlet port of said lubricant air separator means (6), and wherein said auxiliary conduit means comprise an auxiliary supply conduit (12) and an auxiliary return conduit (16) connected between said supply container means (8) and said first valve means (15), said lubricant storage accumulator means comprising an outlet and a conduit (20) including a non-return valve (19) connecting said outlet of said lubricant storage accumulator means to said auxiliary return conduit (16) for venting said lubricant storage accumulator means into said lubricant supply container means (8).