EP1908929A2 - Réservoir de lubrifiant pour un moteur à turbine à gaz pourvu d'un orifice de remplissage ainsi que moteur à turbine à gaz associé - Google Patents

Réservoir de lubrifiant pour un moteur à turbine à gaz pourvu d'un orifice de remplissage ainsi que moteur à turbine à gaz associé Download PDF

Info

Publication number
EP1908929A2
EP1908929A2 EP20070253639 EP07253639A EP1908929A2 EP 1908929 A2 EP1908929 A2 EP 1908929A2 EP 20070253639 EP20070253639 EP 20070253639 EP 07253639 A EP07253639 A EP 07253639A EP 1908929 A2 EP1908929 A2 EP 1908929A2
Authority
EP
European Patent Office
Prior art keywords
oil
housing
filler
gas turbine
turbine engine
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.)
Withdrawn
Application number
EP20070253639
Other languages
German (de)
English (en)
Inventor
Francis Bonacorsi
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Pratt and Whitney Canada Corp
Original Assignee
Pratt and Whitney Canada Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Pratt and Whitney Canada Corp filed Critical Pratt and Whitney Canada Corp
Publication of EP1908929A2 publication Critical patent/EP1908929A2/fr
Withdrawn legal-status Critical Current

Links

Images

Classifications

    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/14—Casings or housings protecting or supporting assemblies within

Definitions

  • the invention relates generally to gas turbine engines and, more particularly, to design and assembly of gas turbine engines.
  • Aero-engines used in multi-engine aircraft typically have right and left installations, that is one or more engines are installed on the right side of the aircraft, and the other(s) on the other side. This often requires the engine to have right-and left-hand configurations, so that equipment is accessible to service personnel, or properly position to interface with aircraft systems, etc.
  • an oil tank filler neck, cap and sight glass for viewing the oil level must be accessible for using and maintaining the engine lubrication system.
  • the engine oil tank housing normally features two oil filler ports and two oil-indicating pads, one on each side of the housing to provide accessibility for either left or right engine configurations).
  • the filler cap, shut-off valve, oil indicator and overfill valve are installed are separately mounted to the oil tank only on one side of the engine (e.g.
  • the present invention provides a gas turbine engine including a compressor and a turbine mounted on bearings to an axial shaft, the compressor having an impeller for pressurizing air in the engine, and a combustion section in fluid communication with pressurized air from the compressor.
  • the gas turbine engine also includes a lubrication system disposed within the engine for lubricating the bearings, the lubrication system having an oil tank mounted within the engine for storing oil, the oil tank being disposed within an oil tank housing having an opening adapted to receive an oil filler housing, the oil filler housing comprising an oil filler port, a shut-off valve and an oil level indicator.
  • the present invention provides an oil filler housing for enabling rapid installation of oil tank components to an oil tank housing that stores oil for a lubrication system of a gas turbine engine.
  • the oil filler housing includes an oil filler port for adding oil to an oil tank within the oil tank housing of the engine, a shut-off valve for preventing oil from escaping when the removable cap is removed, and an oil level indicator for visually indicating an oil level in the oil tank.
  • the present invention provides a method of mounting an oil filler housing to an oil tank housing of a gas turbine engine.
  • the method includes steps of aligning the oil filler housing with a corresponding opening in the oil tank housing where the oil filler housing has an oil filler port for adding oil to an oil tank within the oil tank housing of the engine, a shut-off valve for preventing oil from escaping when a removable cap is removed from the filler port, and an oil level indicator for visually indicating an oil level in the oil tank.
  • the method also includes the step of securing the oil filler housing to the oil tank housing.
  • the invention provides a filler housing for a gas turbine engine, the filler housing comprising: a single housing including a filler port for adding a fluid to a fluid tank of the engine and at least one of a shut-off valve for preventing fluid from escaping when a removable cap is removed, a fluid level indicator, a filler cap, and an overfill valve, the filler housing adapted for direct mounting in an opening provided in a fluid reservoir of the gas turbine engine.
  • a turbofan gas turbine engine incorporating an embodiment of the present invention is presented as an example of the application of the present invention, and includes a housing 10, a core casing 13, a low pressure spool assembly seen generally at 12 which includes a shaft 15 interconnecting a fan assembly 14, a low pressure compressor 16 and a low pressure turbine assembly 18, and a high pressure spool assembly seen generally at 20 which includes a shaft at 25 interconnecting a high pressure compressor assembly 22 and a high pressure turbine assembly 24.
  • the core casing 13 surrounds the low and high pressure spool assemblies 12 and 20 in order to define a main fluid path (not indicated) therethrough.
  • a combustion section 26 having a combustor 28 therein.
  • An accessory gearbox (unindicated) including a oil tank housing 31 is mounted to a lower part of the engine casing.
  • a plurality of bearings are mounted to the shaft 15 to rotationally support the low-pressure and high-pressure compressor and turbine assemblies. These bearings are lubricated and cooled by oil circulated by an engine lubrication system (or "oil system") disposed within the engine.
  • the engine-lubrication system typically includes pumps (both pressure and scavenge pumps), an oil filter, a heat-exchanger, oil-distribution lines and an oil tank disposed within an oil tank housing.
  • FIGS 2-4 show an oil tank housing 31 for use with a lubrication system of a gas turbine engine.
  • the oil tank housing 31 has a rear access cavity 32 on a rear face of the housing for connection to other components of the lubrication system.
  • the oil tank housing 31 also includes an opening 34 on each side of the housing 31 for receiving an oil filler housing 40 (as shown in Figure 4) or a correspondingly shaped blank or plug.
  • the oil filler housing 40 is mounted to the oil tank housing 31 so as to cover, or close off, the opening 34.
  • Openings 34 are provided on both sides of the oil tank housing 31 for dual-engine applications, i.e. so that the oil tank housing 31 can be configured for either left-hand or right-hand engine configurations. Depending on the configuration (left or right engine), one of the two openings will receive the oil filler housing 40 while the opposite one (the unused side) will receive a blank or plug.
  • openings 34 are shown as generally circular, the openings can be of another shape although the shape should be one that is easy to manufacture and which provides access to the interior of the tank housing.
  • the single large opening 34 on each side of the oil tank housing 30 provides ample access to the interior of the oil tank housing for casting cleaning, casting repairs and/or inspections for the casting maker.
  • each opening 34 is surrounded by a generally non-circular lip 36 having three tapped bores 38 for threadedly engaging threaded fasteners (not shown), although the number of bores and their locations can of course be varied.
  • the threaded fasteners are used to threadedly secure the oil filler housing 40 to the lip 36 of the oil tank housing 30.
  • the oil filler housing 40 is aligned with the opening 34 of the oil tank housing 30 such that three bores 41 in a peripheral flange 42 of the oil filler housing align with the tapped bores 38 of the lip 36 of the oil tank housing 30.
  • non-circular lip 36 corresponds in shape to the oil filler housing so as to facilitate relative alignment of these two components.
  • the threaded fasteners are then inserted through the bores 41 in the peripheral flange 42 of the oil filler housing 40 and threaded snugly into the tapped bores of the oil tank housing 30.
  • FIG. 5-6 shows the oil filler housing 40 in accordance with an embodiment of the present invention.
  • the oil filler housing 40 includes an oil filler port 43 (preferably having a removable cap 44) for adding oil to an oil tank within the oil tank housing of the engine.
  • the oil filler housing 40 also includes a shut-off valve 45 for preventing oil from escaping when the removable cap is removed.
  • the oil filler housing 40 further includes an oil level indicator 50 for visually indicating an oil level in the oil tank.
  • the oil level indicator 50 includes a sight glass 52 for viewing the oil level.
  • the sight glass has a maximum fill line (a "max" line) 54 as well as a minimum fill line (a "min” line) 56.
  • the oil filler housing 40 can optionally include an anchor point 46 for receiving a flexible tether 48 for tethering the removable filler cap 44 to the oil filler housing 40.
  • the tether prevents ground crew from losing or dropping the cap when the cap has been unscrewed or otherwise removed from the filler port (i.e. when adding oil to the engine).
  • the tether 48 can be a chain, a cord, or a thin flexible nylon or plastic cable.
  • oil filler housing 40 is a single "modular" unit, it simplifies assembly and maintenance of the engine and also reduces the likelihood of installation errors occurring. In other words, by combining the filler port, oil level indicator and shut-off valve in one integral housing as a single unit, installation and dismantling times (and costs) are reduced.
  • the oil filler housing 40 is constructed such that a top of the oil filler port 43 is higher than the max oil line 52 of the oil level indicator 50, which thus eliminates the need for an overfill valve. Elimination of the overfill valve provides both cost and weight savings for the engine.
  • oil level indicator shut-off valve and filler port
  • the oil filler housing described and illustrated herein represents the best mode of implementing the invention known to the inventors, and therefore it will be appreciated that minor variations, improvements, refinements and substitutions may be made without departing from the invention, including modifying or substituting other types of filler ports, shut-off valves or oil indicators.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Lubrication Details And Ventilation Of Internal Combustion Engines (AREA)
EP20070253639 2006-09-14 2007-09-13 Réservoir de lubrifiant pour un moteur à turbine à gaz pourvu d'un orifice de remplissage ainsi que moteur à turbine à gaz associé Withdrawn EP1908929A2 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US53181306A 2006-09-14 2006-09-14

Publications (1)

Publication Number Publication Date
EP1908929A2 true EP1908929A2 (fr) 2008-04-09

Family

ID=38656614

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20070253639 Withdrawn EP1908929A2 (fr) 2006-09-14 2007-09-13 Réservoir de lubrifiant pour un moteur à turbine à gaz pourvu d'un orifice de remplissage ainsi que moteur à turbine à gaz associé

Country Status (2)

Country Link
EP (1) EP1908929A2 (fr)
WO (1) WO2008031195A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9016068B2 (en) 2012-07-13 2015-04-28 United Technologies Corporation Mid-turbine frame with oil system mounts
CN107939527A (zh) * 2016-10-13 2018-04-20 赛峰航空助推器股份有限公司 涡轮机油箱
WO2019193274A1 (fr) * 2018-04-04 2019-10-10 Safran Aircraft Engines Ensemble moteur pour aeronef presentant un chemin d'alimentation d'un reservoir de compartiment inter-veines d'une turbomachine
FR3082552A1 (fr) * 2018-06-18 2019-12-20 Safran Aircraft Engines Turbomachine d'aeronef a double flux comprenant un reservoir de lubrifiant dans un compartiment inter-veines, ainsi que des moyens ameliores de remplissage du reservoir
US11174755B2 (en) 2018-05-02 2021-11-16 Rolls-Royce Plc Oil tank filling system

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB140734A (en) * 1920-01-08 1920-04-01 John Fielding An improvement in the lubricating apparatus of motor car and the like engines
US1613312A (en) * 1925-05-07 1927-01-04 Oliver C Couts Combined oil gauge and drain device for crank cases
DE4017074A1 (de) * 1990-05-26 1991-11-28 Mann & Hummel Filter Druckregelventil fuer die kurbelgehaeuseentlueftung an einer brennkraftmaschine
US5289900A (en) * 1992-12-28 1994-03-01 United Technologies Corporation Multi-functional service for lubrication tank

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9016068B2 (en) 2012-07-13 2015-04-28 United Technologies Corporation Mid-turbine frame with oil system mounts
CN107939527A (zh) * 2016-10-13 2018-04-20 赛峰航空助推器股份有限公司 涡轮机油箱
CN107939527B (zh) * 2016-10-13 2021-09-07 赛峰航空助推器股份有限公司 涡轮机油箱
WO2019193274A1 (fr) * 2018-04-04 2019-10-10 Safran Aircraft Engines Ensemble moteur pour aeronef presentant un chemin d'alimentation d'un reservoir de compartiment inter-veines d'une turbomachine
FR3079873A1 (fr) * 2018-04-04 2019-10-11 Safran Aircraft Engines Ensemble moteur pour aeronef presentant un chemin d'alimentation d'un reservoir de compartiment inter-veines d'une turbomachine
US11572833B2 (en) 2018-04-04 2023-02-07 Safran Aircraft Engines Aircraft engine assembly with a supply path to an inter-flow compartment tank of turbine engine
US11174755B2 (en) 2018-05-02 2021-11-16 Rolls-Royce Plc Oil tank filling system
FR3082552A1 (fr) * 2018-06-18 2019-12-20 Safran Aircraft Engines Turbomachine d'aeronef a double flux comprenant un reservoir de lubrifiant dans un compartiment inter-veines, ainsi que des moyens ameliores de remplissage du reservoir
US10975741B2 (en) 2018-06-18 2021-04-13 Safran Aircraft Engines Twin-spool aircraft turbomachine comprising a lubricant tank in a compartment between flow streams, and improved means of filling the tank

Also Published As

Publication number Publication date
WO2008031195A1 (fr) 2008-03-20

Similar Documents

Publication Publication Date Title
US10619567B2 (en) Reconfigurable lubrication system for multiple powertrain orientations
US10641128B2 (en) Gas turbine engine oil tank with integrated packaging configuration
EP1908929A2 (fr) Réservoir de lubrifiant pour un moteur à turbine à gaz pourvu d'un orifice de remplissage ainsi que moteur à turbine à gaz associé
US8192143B2 (en) Gearbox assembly
US10072569B2 (en) Gas turbine engine oil tank
EP1496302B1 (fr) Dispositif de lubrification passif et capable de compenser une défaillance
US8893856B2 (en) Gravity scavenged generator with integral engine oil tank
US9611047B2 (en) Arrangement for a tank between a nacelle cowling and a turbomachine
EP2799674A1 (fr) Système d'huile de lubrification pour réducteur de vitesse à engrenages
CA2605108C (fr) Dispositif de distribution d'huile
EP3095976B1 (fr) Système de lubrification destiné à un ensemble de turbine à gaz reconfigurable
US20150292414A1 (en) Air turbine starters having oil feed shutoff valves and gas turbine engines including the same
EP2789806A1 (fr) Procédés et systèmes pour empêcher une fuite d'huile de lubrification dans des turbines à gaz
EP3670863B1 (fr) Système de lubrification auxiliaire avec soupape de gestion de flux
US20160376923A1 (en) Pump for a turbine engine
US10816007B2 (en) Oil tank installation in gas turbine engine
US11035294B2 (en) Turbomachine with double flow and its lubricant reservoir
CA2743281C (fr) Systeme de lubrification de moteur d'aeronef
US9777747B2 (en) Turbocharger with dual-use mounting holes
EP3339583B1 (fr) Système de lubrification de soufflante distribué
US20120263614A1 (en) Housingless positive displacement pump assembly
CN210291374U (zh) 一种带副泵的轻质机油泵
CN109141851A (zh) 独立式压缩机润滑系统检测平台
CA2967438A1 (fr) Assemblage de reservoir d'huile destine a un moteur de turbine a gaz
INE Operators Manual

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK RS

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN WITHDRAWN

18W Application withdrawn

Effective date: 20090120