EP0692066A1 - Gasturbinen-triebwerk mit lagerkammern und sperrluftkammern - Google Patents
Gasturbinen-triebwerk mit lagerkammern und sperrluftkammernInfo
- Publication number
- EP0692066A1 EP0692066A1 EP94911189A EP94911189A EP0692066A1 EP 0692066 A1 EP0692066 A1 EP 0692066A1 EP 94911189 A EP94911189 A EP 94911189A EP 94911189 A EP94911189 A EP 94911189A EP 0692066 A1 EP0692066 A1 EP 0692066A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- sealing air
- compressor
- chamber
- pressure
- air flow
- 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
- 238000007789 sealing Methods 0.000 claims description 75
- 230000004888 barrier function Effects 0.000 abstract 1
- 239000003921 oil Substances 0.000 description 11
- 239000010687 lubricating oil Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 238000011144 upstream manufacturing Methods 0.000 description 2
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000009931 harmful effect Effects 0.000 description 1
- 229910052749 magnesium Inorganic materials 0.000 description 1
- 239000011777 magnesium Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
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
- F01D25/183—Sealing means
Definitions
- the invention relates to a gas turbine engine, in particular a flight gas turbine, with a compressor-side bearing chamber and a turbine-side bearing chamber, with the sealing air chambers surrounding the oil-supplied bearing chambers, which are provided by a low-pressure compressor or fan and a high-pressure compressor a sealing air stream are supplied, which at least partially reaches the associated storage chamber via labyrinth seals and is discharged from there via an oil separator, especially in the area.
- a gas turbine engine in particular a flight gas turbine, with a compressor-side bearing chamber and a turbine-side bearing chamber, with the sealing air chambers surrounding the oil-supplied bearing chambers, which are provided by a low-pressure compressor or fan and a high-pressure compressor a sealing air stream are supplied, which at least partially reaches the associated storage chamber via labyrinth seals and is discharged from there via an oil separator, especially in the area.
- the seals provided in the bearing chambers for the shafts of a gas turbine engine between the wall of the bearing chamber and the shaft passing through them are necessary in order to prevent the escape of lubricating oil or an oil mist into the compressor or into the turbine.
- This seal must be made contact-free, so that labyrinth seals are usually used, but which are additionally flowed through by a sealing air flow in order to achieve an optimal sealing effect.
- This sealing air flow comes from a sealing air chamber surrounding the storage chamber via the labyrinth seals into the storage chamber and is preferably discharged from there into the environment via an oil separator, but could also be used in a different manner.
- the pressure in the sealing air chamber must be a certain amount above that after the storage chamber. It is therefore customary to supply the sealing air chambers with a sealing air flow from the low-pressure compressor, which can also be designed as a fan, or from the high-pressure compressor.
- the low-pressure compressor which can also be designed as a fan, or from the high-pressure compressor.
- operating points can occur in which the pressure provided by the low-pressure compressor or fan is insufficient, a sealing air flow overcoming the flow resistances, for example in the labyrinth seals via the sealing air chamber and the storage chamber and continue to pump into the environment via an oil separator.
- GB-B-702 931 therefore proposes to branch off the sealing air flow from the high-pressure compressor in these cases.
- the sealing air chamber on the compressor side is supplied with sealing air by the low pressure compressor or fan and the sealing air chamber on the turbine side is supplied with sealing air by the high pressure compressor, and that the sealing air flow emerging from the bearing chamber on the compressor side is ejected in an ejector from the bearing chamber on the turbine side emerging sealing air flow is added.
- the oil separator can be provided downstream of the ejector.
- the compressor-side bearing chamber 1 is surrounded by a compressor-side sealing air chamber 11 and the turbine-side bearing chamber 2 is surrounded by a turbine-side sealing air chamber 12.
- Non-contact labyrinth seals 13 are provided in the area of the passages through the walls 5, 6 through the walls of the storage chambers 1, 2 or sealing air chambers 3, 4. These labyrinth seals 13 are intended to prevent the lubricating oil located in the bearing chambers from reaching the compressor chamber or the turbine chamber.
- a sealing air flow is directed from the respective sealing air chamber 11, 12 via the associated bearing chamber 1, 2 into the environment to support this sealing effect - this is denoted by the reference number 14.
- This ejector 18 can also be referred to as a suction jet pump and is connected to the discharge line 16 in such a way that in this ejector 18 the sealing air flow supplied via the discharge line 16 is accelerated such that the sealing air flow coming into the ejector via the discharge line 15 from the compressor-side storage chamber 1 is suctioned off.
- the pressure level, which is still relatively high at all operating points, of the sealing air flow discharged via the discharge line 16 of the turbine-side bearing chamber 2 is thus used to convey the sealing air flow through the compressor-side bearing chamber 1.
- the pressure level of the sealing air flow carried in the discharge line 16 is always sufficiently high, since the sealing air flow for the turbine-side bearing chamber is always branched off from the high-pressure compressor via the supply line 17.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Description
Claims
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB939306890A GB9306890D0 (en) | 1993-04-01 | 1993-04-01 | A gas turbine engine with bearing chambers and barrier air chambers |
GB9306890 | 1993-04-01 | ||
PCT/EP1994/000854 WO1994023184A1 (de) | 1993-04-01 | 1994-03-18 | Gasturbinen-triebwerk mit lagerkammern und sperrluftkammern |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0692066A1 true EP0692066A1 (de) | 1996-01-17 |
EP0692066B1 EP0692066B1 (de) | 1997-06-04 |
Family
ID=10733219
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP94911189A Expired - Lifetime EP0692066B1 (de) | 1993-04-01 | 1994-03-18 | Gasturbinen-triebwerk mit lagerkammern und sperrluftkammern |
Country Status (6)
Country | Link |
---|---|
US (1) | US5611661A (de) |
EP (1) | EP0692066B1 (de) |
CA (1) | CA2159634C (de) |
DE (1) | DE59403036D1 (de) |
GB (1) | GB9306890D0 (de) |
WO (1) | WO1994023184A1 (de) |
Families Citing this family (31)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19956919A1 (de) * | 1999-11-26 | 2001-05-31 | Rolls Royce Deutschland | Gasturbinen-Triebwerk mit einer Lagerkammer |
US6582187B1 (en) * | 2000-03-10 | 2003-06-24 | General Electric Company | Methods and apparatus for isolating gas turbine engine bearings |
JP4375883B2 (ja) | 2000-06-02 | 2009-12-02 | 本田技研工業株式会社 | ガスタービンエンジンの軸受へのシールエア供給装置 |
US6470666B1 (en) * | 2001-04-30 | 2002-10-29 | General Electric Company | Methods and systems for preventing gas turbine engine lube oil leakage |
US20030097872A1 (en) * | 2001-11-29 | 2003-05-29 | Granitz Charles Robert | System for reducing oil consumption in gas turbine engines |
US6799112B1 (en) * | 2003-10-03 | 2004-09-28 | General Electric Company | Methods and apparatus for operating gas turbine engines |
US7093418B2 (en) * | 2004-04-21 | 2006-08-22 | Honeywell International, Inc. | Gas turbine engine including a low pressure sump seal buffer source and thermally isolated sump |
JP4675638B2 (ja) * | 2005-02-08 | 2011-04-27 | 本田技研工業株式会社 | ガスタービンエンジンの2次エア供給装置 |
US7836675B2 (en) * | 2006-02-21 | 2010-11-23 | General Electric Company | Supercore sump vent pressure control |
US8245818B2 (en) * | 2007-10-23 | 2012-08-21 | Pratt & Whitney Canada Corp. | Gas turbine oil scavenging system |
US8172512B2 (en) * | 2008-04-23 | 2012-05-08 | Hamilton Sundstrand Corporation | Accessory gearbox system with compressor driven seal air supply |
GB201107256D0 (en) | 2011-05-03 | 2011-06-15 | Rolls Royce Plc | Gas cooler and method for cooling gas |
GB2495092B (en) * | 2011-09-28 | 2014-01-01 | Rolls Royce Plc | Sealing arrangement |
US8956106B2 (en) * | 2011-12-20 | 2015-02-17 | General Electric Company | Adaptive eductor system |
GB201200290D0 (en) * | 2012-01-10 | 2012-02-22 | Rolls Royce Plc | Gas turbine engine buffer seals |
US20130192251A1 (en) * | 2012-01-31 | 2013-08-01 | Peter M. Munsell | Buffer system that communicates buffer supply air to one or more portions of a gas turbine engine |
US10502135B2 (en) * | 2012-01-31 | 2019-12-10 | United Technologies Corporation | Buffer system for communicating one or more buffer supply airs throughout a gas turbine engine |
US9097180B2 (en) | 2013-01-28 | 2015-08-04 | General Electric Company | Apparatus and method for reducing oil mist ingestion in a heavy duty gas turbine engine |
GB201303636D0 (en) * | 2013-03-01 | 2013-04-17 | Rolls Royce Plc | Chamber fluid removal system |
FR3016661B1 (fr) * | 2014-01-23 | 2019-05-03 | Safran Aircraft Engines | Enceinte de palier d'une turbomachine |
EP2975227B1 (de) * | 2014-07-14 | 2018-10-03 | Rolls-Royce Corporation | Schmiersystem für gasturbinenmotoren |
EP3186487A1 (de) * | 2014-08-28 | 2017-07-05 | Turboden S.p.A. | Dichtungsanordnung in einer turbine und verfahren zur begrenzung von betriebsflüssigkeit |
EP3186488A1 (de) * | 2014-08-28 | 2017-07-05 | Turboden S.p.A. | Turbine mit einer dichtungsanordnung, anlage mit organischem rankine-prozess und verfahren zur einschränkung der betriebsflüssigkeit |
RU2596896C1 (ru) * | 2015-06-02 | 2016-09-10 | Открытое акционерное общество "Уфимское моторостроительное производственное объединение" ОАО "УМПО" | Двухконтурный газотурбинный двигатель |
US10318903B2 (en) | 2016-05-06 | 2019-06-11 | General Electric Company | Constrained cash computing system to optimally schedule aircraft repair capacity with closed loop dynamic physical state and asset utilization attainment control |
US10550724B2 (en) | 2016-10-11 | 2020-02-04 | General Electric Company | System and method for the pressurization of a sump of a gas turbine engine |
PL421044A1 (pl) * | 2017-03-30 | 2018-10-08 | General Electric Company | Układ oraz sposób dla pompy strumieniowej silnika zasilanej przez zamienny układ regulacji przepływu powietrza |
US10927845B2 (en) * | 2017-05-24 | 2021-02-23 | The Boeing Company | Seal assembly and method for reducing aircraft engine oil leakage |
RU2699870C1 (ru) * | 2018-08-03 | 2019-09-11 | Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") | Охлаждаемая турбина двухконтурного газотурбинного двигателя |
GB201911980D0 (en) * | 2019-08-21 | 2019-10-02 | Rolls Royce Plc | Gas turbine engine |
CN115795705B (zh) * | 2022-10-19 | 2024-01-02 | 中国航发沈阳发动机研究所 | 一种航空发动机空气系统引气管路及其流阻特性设计方法 |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB702931A (en) * | 1951-04-18 | 1954-01-27 | Bristol Aeroplane Co Ltd | Improvements in or relating to rotary machines comprising fluid compressing means |
US3527054A (en) * | 1969-01-23 | 1970-09-08 | Gen Electric | Pressurization of lubrication sumps in gas turbine engines |
US3722624A (en) * | 1971-06-07 | 1973-03-27 | Gen Electric | Bearing seal and oil tank ventilation system |
GB2111607B (en) * | 1981-12-08 | 1985-09-18 | Rolls Royce | Bearing chamber pressurisation system for a machine |
DE3826217A1 (de) * | 1988-08-02 | 1990-02-08 | Mtu Muenchen Gmbh | Gasturbine mit einer verdichterseitigen lagerkammer |
-
1993
- 1993-04-01 GB GB939306890A patent/GB9306890D0/en active Pending
-
1994
- 1994-03-18 DE DE59403036T patent/DE59403036D1/de not_active Expired - Fee Related
- 1994-03-18 WO PCT/EP1994/000854 patent/WO1994023184A1/de active IP Right Grant
- 1994-03-18 US US08/530,175 patent/US5611661A/en not_active Expired - Lifetime
- 1994-03-18 CA CA002159634A patent/CA2159634C/en not_active Expired - Fee Related
- 1994-03-18 EP EP94911189A patent/EP0692066B1/de not_active Expired - Lifetime
Non-Patent Citations (1)
Title |
---|
See references of WO9423184A1 * |
Also Published As
Publication number | Publication date |
---|---|
CA2159634C (en) | 1999-08-24 |
WO1994023184A1 (de) | 1994-10-13 |
EP0692066B1 (de) | 1997-06-04 |
US5611661A (en) | 1997-03-18 |
CA2159634A1 (en) | 1994-10-13 |
DE59403036D1 (de) | 1997-07-10 |
GB9306890D0 (en) | 1993-06-02 |
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