GB2436425A - Lubrication system for aircraft jet engine - Google Patents
Lubrication system for aircraft jet engine Download PDFInfo
- Publication number
- GB2436425A GB2436425A GB8924909A GB8924909A GB2436425A GB 2436425 A GB2436425 A GB 2436425A GB 8924909 A GB8924909 A GB 8924909A GB 8924909 A GB8924909 A GB 8924909A GB 2436425 A GB2436425 A GB 2436425A
- Authority
- GB
- United Kingdom
- Prior art keywords
- oil
- pump
- scoop
- delivery system
- reservoir
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000005461 lubrication Methods 0.000 title description 6
- 230000002000 scavenging effect Effects 0.000 claims abstract description 12
- 230000000694 effects Effects 0.000 claims abstract description 5
- 238000005086 pumping Methods 0.000 claims abstract description 5
- 230000009467 reduction Effects 0.000 description 2
- 230000002411 adverse Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000001050 lubricating effect Effects 0.000 description 1
- 238000007726 management method Methods 0.000 description 1
- 238000013021 overheating Methods 0.000 description 1
- 230000005514 two-phase flow Effects 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/18—Lubricating arrangements
- F01D25/20—Lubricating arrangements using lubrication pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16N—LUBRICATING
- F16N17/00—Lubrication of machines or apparatus working under extreme conditions
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/60—Fluid transfer
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Abstract
For an aircraft jet engine, a pumped oil delivery system for delivering oil to moving parts includes a scoop delivery pump 10 and an accumulator oil reservoir 12 to maintain oil feed to type pump at all times. The system includes a first line 24 to feed oil from the scoop pump to the oil reservoir, a second line 26 to return oil from the oil reservoir to the scoop pump, and air pressure means for pressurising the oil within the oil reservoir so as to maintain a continuous feed of oil to the pump. The system further includes line means 18 for delivering oil from the scoop pump to each said moving part and line means 20, 22 for returning oil from said moving part to the scoop pump. Moving parts include a self scavenging gear box utilising the centrifugal pumping action of its gears to return oil to the scoop pump, and self scavenging bearing chambers using centrifugal effects of their rotating parts also to return oil to the scoop pump.
Description
<p>IMPROVEMENTS IN OR RELATING TO LUBRICATION SYSTEMS FOR</p>
<p>AIRCRAFT ENGINES</p>
<p>This invention concerns improvements in or relating to lubrication systems, in particular lubrication systems for aircraft engines.</p>
<p>Lubricating the moving parts of aircraft engines, particularly engines used in jet fighter aircraft, presents special problems. Fighter aircraft in combat situations frequently operate at or near the limits of their performance and may, under conditions of high "g" forces and/or high altitude, experience temporary loss of fuel pressure or lubrication in certain parts of the -engine or its associated gear boxes, with a consequent overheating of engine or gear box parts and a possible reduction in performance. Particular adverse effects which may be experienced under combat conditions include loss of pressure in the oil pump, and oil hiding, that is, a quantity of oil is unused because it remains t'hidden" and is not circulated through the moving parts.</p>
<p>It is an object of the present invention to provide for an aircraft jet engine a pumped oil system which is insensitive to aircraft attitude or altitude and in which loss of pressure in the pump is eliminated.</p>
<p>According to the present invention there is provided, for an aircraft jet engine, a pumped oil delivery system for delivering oil to moving parts, the system including in cooperative relationship a scoop delivery pump and an accumulator oil reservoir to maintain oil feed to the pump at all times.</p>
<p>Preferably, the oil delivery system includes a first line to feed oil from the scoop pump to the oil reservoir, a second line to return oil from the oil reservoir to the scoop pump, and means for pressurising the oil within the oil reservoir so as to maintain a continuous feed of oil to the pump.</p>
<p>Preferably, the means for pressurising the oil within the oil reservoir is air pressure.</p>
<p>Preferably, the oil delivery system includes line means for delivering oil from the scoop pump to each said moving part and line means for returning oil from said moving part to the scoop pump.</p>
<p>A said moving part may be a self scavenging gear box utilising the centrifugal pumping action of the gears to return oil to the scoop pump.</p>
<p>A said moving part may be a self scavenging bearing chamber using centrifugal effects of its rotating parts to return oil to the scoop pump.</p>
<p>The invention will now be described by way of example only with reference to the accompanying Figure 1. which is a block diagram representation of a lubrication system for a jet aircraft engine.</p>
<p>Referring to Figure 1 there is shown a scoop delivery pump 10, an accumulator oil reservoir 12, a self scavenging gear box 14, and a self scavenging bearing chamber 16.</p>
<p>A primary scoop line 18 takes oil from the pump 10 and delivers the oil to the gear box 14 and the bearing chamber 16 (of which there may be more than one). First and second return lines 20, 22 return oil from the gear box 14 and the bearing chamber 16 respectively to the pump 10.</p>
<p>A secondary scoop line 24 takes oil from the pump 10 and delivers it to the accumulator reservoir 12 from when a third return line 26 returns oil to the pump.</p>
<p>The accumulator reservoir 12 is provided by a piston 28 sliding in the bore of a cylinder. The space between the piston crown and the end of the cylinder is filled with oil fed into the cylinder from the secondary scoop line 24. The oil in the cylinder space is pressurised by compressed air acting against the base of the piston. Consequently, oil fed into the reservoir 12 from the pump 10 is returned to the pump under positive pressure and loss of pressure in the pump from whatever cause (altitude, attitude, or "g" forces) is eliminated. The air pressure may be controlled by suitable valve means, or by air bled from a compressor stage, to ensure that the air pressure acting on the piston is not so great that the pump is unable to pump oil into the reservoir.</p>
<p>The gear box 14 is a self scavenging gear box whereby all the oil used is scavenged by the centrifugal action of the gear train within and returned to the scoop pump via line 20. Likewise, the bearing chamber 16 is a self scavenging chamber in which the centrifugal action of the bearings returns oil to the pump 10 via line 22.</p>
<p>It is convenient to have the reservoir 12 incorporated as an integral part of the gear box 14, thereby saving bulk and weight.</p>
<p>The invention provides an oil management system for a jet aircraft engine in which oil is pumped at all times to and from all chambers; problems associated with two phase flow are greatly reduced and possibly eliminated; the bulk size of the oil system is reduced, hence achieving reductions in weight and cost; oil contents is reduced to the capacity of usable oil since oil hiding is eliminated (a consequence of the positive pumping to and from all chambers); and loss of pressure pump prime is eliminated as the system is insensitive to attitude and altitude.</p>
Claims (1)
- <p>S</p><p>CLAIMS</p><p>1. For an aircraft jet engine, a pumped oil delivery system for delivering oil to moving parts, the system including in cooperative relationship a scoop delivery pump and an accumulator oil reservoir to maintain oil feed to the pump at all times.</p><p>2. An oil delivery ystem as claimed in claim 1 wherein the oil delivery system includes a first line to feed oil from the scoop pump to the oil reservoir, a second line to return oil from the oil reservoir to the scoop pump, and means for pressurising the oil within the oil reservoir so as to maintain a continuous feed of oil to the pump.</p><p>3. An oil delivery system as claimed in claim 2 wherein the means for pressurising the oil within the oil reservoir is air pressure.</p><p>4. An oil delivery system as claimed in claim 1 wherein the system includes line means for delivering oil from the scoop pump to each said moving part and line means for returning oil from said moving part to the scoop pump.</p><p>5. An oil delivery system as claimed in claim 4 wherein said moving part is a self scavenging gear box utilising the centrifugal pumping action of its gears to return oil to the scoop pump.</p><p>6. An oil delivery system as claimed in claim 4 wherein said moving part is a self scavenging bearing chamber using centrifugal effects of its rotating parts to return oil to the scoop pump.</p><p>7. For an aircraft jet engine, a pumped oil delivery system for delivering oil to moving parts, substantially as herein described with reference to the accompanying Figure 1.</p><p>Amendments to the claims have been filed as follows 1. In combination with an aircraft jet engine, a pumped oil delivery system for delivering oil to moving parts of the engine, the system including in cooperative relationship a scoop delivery pump, an oil reservoir, a first line to feed oil from the scoop pump to the oil reservoir, a second line to return oil from the oil reservoir to the scoop pump, and means for pressurising the oil within the oil reservoir so as to maintain a continuous feed of oil to the pump.</p><p>2. In combination with an aircraft jet engine, an oil delivery system as claimed in claim 1 wherein the means for pressurising the oil within the oil reservoir is air pressure.</p><p>3. In combination with an aircraft jet engine, an oil delivery system as claimed in claim 1 wherein the system includes line means for delivering oil from the scoop pump to each said moving part and line means for returning oil from said moving part to the scoop pump.</p><p>4. In combination with an aircraft jet engine, an oil delivery system as claimed in claim 3 wherein said moving part is a self scavenging gear box utilising the centrifugal pumping action of its gears to return oil to the scoop pump.</p><p>5. In combination with an aircraft jet engine, an oil delivery system as claimed in claim 3 wherein said moving part is a self scavenging bearing chamber using centrifugal effects of its rotating parts to return oil to the scoop pump.</p><p>6. An aircraft jet engine including a pumped oil delivery system for delivering oil to moving parts, substantially as herein described with reference to the accompanying Figure 1.</p>
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB8924909A GB2436425B (en) | 1989-11-03 | 1989-11-03 | Improvements in or relating to lubrication systems for aircraft engines |
US07/605,168 US7905325B1 (en) | 1989-11-03 | 1990-10-12 | Relating to lubrication system for aircraft engines |
DE4034012A DE4034012A1 (en) | 1989-11-03 | 1990-10-25 | Lubricating system for aircraft engines |
IT021897A IT9021897A1 (en) | 1989-11-03 | 1990-10-29 | REFINEMENTS MADE TO LUBRICATION SYSTEMS FOR AVIATION ENGINES |
FR9013507A FR2894618A1 (en) | 1989-11-03 | 1990-10-31 | Lubricator for moving parts of aircraft jet engines, comprises oil feed pump, accumulation reservoir, piping and reservoir interior pressurizing device to maintain continuous oil supply to pump |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB8924909A GB2436425B (en) | 1989-11-03 | 1989-11-03 | Improvements in or relating to lubrication systems for aircraft engines |
Publications (3)
Publication Number | Publication Date |
---|---|
GB8924909D0 GB8924909D0 (en) | 2007-03-28 |
GB2436425A true GB2436425A (en) | 2007-09-26 |
GB2436425B GB2436425B (en) | 2008-06-11 |
Family
ID=37909045
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB8924909A Expired - Lifetime GB2436425B (en) | 1989-11-03 | 1989-11-03 | Improvements in or relating to lubrication systems for aircraft engines |
Country Status (5)
Country | Link |
---|---|
US (1) | US7905325B1 (en) |
DE (1) | DE4034012A1 (en) |
FR (1) | FR2894618A1 (en) |
GB (1) | GB2436425B (en) |
IT (1) | IT9021897A1 (en) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9051878B2 (en) | 2011-06-22 | 2015-06-09 | Hamilton Sundstrand Corporation | Engine bearing compartment |
US9470303B2 (en) | 2013-10-08 | 2016-10-18 | Sikorsky Aircraft Corporation | Self scavenging gear shield |
AU2015200532A1 (en) | 2014-02-05 | 2015-08-20 | Orbital Australia Pty Ltd | Engine Lubrication System |
US9989083B2 (en) | 2015-05-26 | 2018-06-05 | Pratt & Whitney Canada Corp. | Seal and bearing assembly for a gas turbine engine and method of assembling same |
US11428163B2 (en) * | 2018-12-18 | 2022-08-30 | Raytheon Technologies Corporation | Two tier lubrication system |
US20230349326A1 (en) * | 2022-04-29 | 2023-11-02 | General Electric Company | Passive auxiliary lubrication system |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1398456A (en) * | 1972-11-08 | 1975-06-25 | Bbc Sulzer Turbomaschinen | Gas turbine engines |
GB1497624A (en) * | 1975-08-07 | 1978-01-12 | Mtu Muenchen Gmbh | Gas turbine system |
GB2042649A (en) * | 1979-02-19 | 1980-09-24 | Avco Corp | Lubrication System |
GB2084266A (en) * | 1980-09-26 | 1982-04-07 | Rolls Royce | Oil system for aircraft gas turbine engine |
GB2204642A (en) * | 1987-05-06 | 1988-11-16 | Mtu Muenchen Gmbh | Reduction gear lubrication in a propfan turbo propulsion unit |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4157744A (en) * | 1977-07-18 | 1979-06-12 | Capriotti Lawrence J | Lubricating and cooling engine system component |
US4648485A (en) * | 1985-10-04 | 1987-03-10 | United Technologies Corporation | Radial scoop construction |
-
1989
- 1989-11-03 GB GB8924909A patent/GB2436425B/en not_active Expired - Lifetime
-
1990
- 1990-10-12 US US07/605,168 patent/US7905325B1/en not_active Expired - Fee Related
- 1990-10-25 DE DE4034012A patent/DE4034012A1/en active Pending
- 1990-10-29 IT IT021897A patent/IT9021897A1/en unknown
- 1990-10-31 FR FR9013507A patent/FR2894618A1/en not_active Withdrawn
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB1398456A (en) * | 1972-11-08 | 1975-06-25 | Bbc Sulzer Turbomaschinen | Gas turbine engines |
GB1497624A (en) * | 1975-08-07 | 1978-01-12 | Mtu Muenchen Gmbh | Gas turbine system |
GB2042649A (en) * | 1979-02-19 | 1980-09-24 | Avco Corp | Lubrication System |
GB2084266A (en) * | 1980-09-26 | 1982-04-07 | Rolls Royce | Oil system for aircraft gas turbine engine |
GB2204642A (en) * | 1987-05-06 | 1988-11-16 | Mtu Muenchen Gmbh | Reduction gear lubrication in a propfan turbo propulsion unit |
Also Published As
Publication number | Publication date |
---|---|
IT9021897A0 (en) | 1990-10-29 |
DE4034012A1 (en) | 2009-02-26 |
IT9021897A1 (en) | 1991-05-04 |
US7905325B1 (en) | 2011-03-15 |
FR2894618A1 (en) | 2007-06-15 |
GB2436425B (en) | 2008-06-11 |
GB8924909D0 (en) | 2007-03-28 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PE20 | Patent expired after termination of 20 years |
Expiry date: 20091102 |