EP0151071B1 - Dispositif d'étanchéité périphérique d'aubage de compresseur axial - Google Patents
Dispositif d'étanchéité périphérique d'aubage de compresseur axial Download PDFInfo
- Publication number
- EP0151071B1 EP0151071B1 EP19850400112 EP85400112A EP0151071B1 EP 0151071 B1 EP0151071 B1 EP 0151071B1 EP 19850400112 EP19850400112 EP 19850400112 EP 85400112 A EP85400112 A EP 85400112A EP 0151071 B1 EP0151071 B1 EP 0151071B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- grooves
- blades
- tip
- sealing device
- blading
- 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.)
- Expired
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/08—Sealings
- F04D29/16—Sealings between pressure and suction sides
- F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
- F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
- F04D29/526—Details of the casing section radially opposing blade tips
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
- F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
- F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
Definitions
- the invention relates to a peripheral sealing device for blading an axial compressor, the fixed ring or the wall of the casing surrounding the blading comprising circumferential grooves.
- This device has the disadvantage of requiring a combined cutting of the blade heads and steps, resulting in delicate machining and a high cost price.
- French patent 2,432,105 retains the principle of the formation of discontinuities on the inner wall of the compressor casing facing the blading but no longer requires cutting of the blade heads.
- the discontinuities consist of circumferential grooves and / or axially extending cavities. These discontinuities are machined in the bottom of a larger circumferential cavity provided in the envelope. Under the effect of expansions and centrifugal elongation, the ends of the blade heads penetrate into the cavity and rotate with a slight clearance in front of the grooves.
- the device described would allow an appreciable increase in the yield, but experience seems to indicate a contrary result, due to the separation of the flow which occurs on the descending step of the peripheral corridor in which the blade heads emerge.
- French patent 2,440,467 includes, like the previous patent, grooves but these open out at the inside wall of the casing and consequently the ends of the blade heads are no longer embedded.
- the aim is to thicken the boundary layer which forms and which has the effect of thwarting the leakage flow at the tips of the blades and to direct this boundary layer in the direction of the leak which prevails at the tips of the blades.
- the increase in the thickness of the boundary layer leads to a greater susceptibility to dropping, which is undesirable.
- the device according to the invention proceeds from the systems described above and in order to overcome the drawbacks mentioned, it comprises a plurality of circumferential grooves whose profile in section is that of a right triangle of which one side of the right angle is perpendicular to the axis of the compressor and the other side of the right angle of which is parallel to the said axis, the hypotenuse of the right triangle forms a divergent face to the flow of the fluid.
- FIG. 1 shows a partial perspective view of a compressor stage.
- the vane 1 consists in a known manner of vanes 2 held at the periphery of a rotor disc 3.
- the vanes 2 move in front of a ring 4 held in the wall of the compressor housing (not shown).
- This ring has circumferential grooves 5, the shape and distribution of which will be specified later.
- the ring is made of an abradable or non-abradable material in front of which the rectilinear heads 6 of the blades move with very little play.
- the flow of the fluid stream is indicated by the arrows 7.
- the purpose of the circumferential grooves, constituting the sealing device according to the invention, is to create a succession of mini divergent and radial projections, these projections being oriented facing the flow.
- the general sectional profile of a groove is that of a right triangle, one side of the right angle of which is perpendicular to the axis of the ring and the other of which is parallel to said axis.
- the grooves are of the same dimensions and uniformly distributed over the width of the ring.
- the grooving width separating the start 8 of the first groove (or upstream groove) of the projection 9 of the last groove (or downstream groove) must be slightly greater than the depth p of the blade, this depth being measured between two radial planes tangent to the top of the leading and trailing edges.
- the depth of the successive diverging points is variable and increases from upstream to downstream, the axial width of the groove retaining the same dimension.
- Figures 3 and 4 show des.applications in which the divergents are not uniformly distributed on the ring and whose depth and possibly the width of the grooves vary according to their position, in fact the influence of the radial clearance is more or less sensitive at determined locations in the ring and it is then necessary to compensate for these anomalies by an irregular arrangement of the divergents whose action is controlled by their depth.
- Figure 5 is an example of application in which similar grooves are arranged symmetrically with respect to the radial plane of symmetry of the blade.
- the grooves forming the divergent parts and the projections consist of one or more helical grooves. These helical grooves help to deflect the radial component of the velocity in the normal direction of flow and to oppose the reverse flow.
- the ring 4 When the ring 4 is made of an abradable material, this can be molded or machined in the form of removable cartridges as described in French patent 2,452,601. This embodiment has greater ease of maintenance and offers a effective damping of crankcase vibrations.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR8401530A FR2558900B1 (fr) | 1984-02-01 | 1984-02-01 | Dispositif d'etancheite peripherique d'aubage de compresseur axial |
FR8401530 | 1984-02-01 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0151071A2 EP0151071A2 (fr) | 1985-08-07 |
EP0151071A3 EP0151071A3 (en) | 1985-09-25 |
EP0151071B1 true EP0151071B1 (fr) | 1988-08-03 |
Family
ID=9300660
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19850400112 Expired EP0151071B1 (fr) | 1984-02-01 | 1985-01-24 | Dispositif d'étanchéité périphérique d'aubage de compresseur axial |
Country Status (5)
Country | Link |
---|---|
US (1) | US4767266A (ja) |
EP (1) | EP0151071B1 (ja) |
JP (1) | JPS60243400A (ja) |
DE (1) | DE3564147D1 (ja) |
FR (1) | FR2558900B1 (ja) |
Families Citing this family (39)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE19619438B4 (de) * | 1996-05-14 | 2005-04-21 | Alstom | Wärmestausegment für eine Turbomaschine |
US5791871A (en) * | 1996-12-18 | 1998-08-11 | United Technologies Corporation | Turbine engine rotor assembly blade outer air seal |
US6572114B1 (en) * | 1997-09-22 | 2003-06-03 | Mitsubishi Heavy Industries, Ltd. | Seal ring for steam turbine |
US6146089A (en) * | 1998-11-23 | 2000-11-14 | General Electric Company | Fan containment structure having contoured shroud for optimized tip clearance |
US6527509B2 (en) * | 1999-04-26 | 2003-03-04 | Hitachi, Ltd. | Turbo machines |
US6234747B1 (en) * | 1999-11-15 | 2001-05-22 | General Electric Company | Rub resistant compressor stage |
US6350102B1 (en) * | 2000-07-19 | 2002-02-26 | General Electric Company | Shroud leakage flow discouragers |
JP3862137B2 (ja) * | 2000-09-20 | 2006-12-27 | 淳一 黒川 | ターボ形水力機械 |
US6499940B2 (en) * | 2001-03-19 | 2002-12-31 | Williams International Co., L.L.C. | Compressor casing for a gas turbine engine |
WO2004113770A2 (en) * | 2003-06-20 | 2004-12-29 | Elliott Company | Swirl-reversal abradable labyrinth seal |
KR100568183B1 (ko) * | 2004-01-08 | 2006-04-05 | 삼성전자주식회사 | 터보압축기 |
US20050200080A1 (en) * | 2004-03-10 | 2005-09-15 | Siemens Westinghouse Power Corporation | Seal for a turbine engine |
JP4928747B2 (ja) * | 2005-06-24 | 2012-05-09 | 三菱重工業株式会社 | 渦励振抑制構造 |
GB0526011D0 (en) * | 2005-12-22 | 2006-02-01 | Rolls Royce Plc | Fan or compressor casing |
US8100640B2 (en) | 2007-10-25 | 2012-01-24 | United Technologies Corporation | Blade outer air seal with improved thermomechanical fatigue life |
US20100030365A1 (en) * | 2008-07-30 | 2010-02-04 | Pratt & Whitney | Combined matching and inspection process in machining of fan case rub strips |
GB2477745A (en) * | 2010-02-11 | 2011-08-17 | Rolls Royce Plc | Compressor Casing |
US9206904B2 (en) | 2010-07-08 | 2015-12-08 | Siemens Energy, Inc. | Seal including flexible seal strips |
US8690158B2 (en) * | 2010-07-08 | 2014-04-08 | Siemens Energy, Inc. | Axially angled annular seals |
GB2483060B (en) | 2010-08-23 | 2013-05-15 | Rolls Royce Plc | A turbomachine casing assembly |
GB2487900B (en) * | 2011-02-03 | 2013-02-06 | Rolls Royce Plc | A turbomachine comprising an annular casing and a bladed rotor |
DE102012200883B4 (de) * | 2012-01-23 | 2015-12-03 | MTU Aero Engines AG | Strömungsmaschinen-Dichtungsanordnung |
FR2989742B1 (fr) * | 2012-04-19 | 2014-05-09 | Snecma | Carter de compresseur a cavites a forme amont optimisee |
US9777582B2 (en) | 2012-07-03 | 2017-10-03 | United Technologies Corporation | Tip leakage flow directionality control |
US9951629B2 (en) * | 2012-07-03 | 2018-04-24 | United Technologies Corporation | Tip leakage flow directionality control |
US9957817B2 (en) * | 2012-07-03 | 2018-05-01 | United Technologies Corporation | Tip leakage flow directionality control |
FR2994718B1 (fr) * | 2012-08-27 | 2017-04-21 | Snecma | Carter a traitements de carter arasants |
WO2014091599A1 (ja) * | 2012-12-13 | 2014-06-19 | 株式会社日立製作所 | 回転流体機械 |
EP2961940B1 (en) * | 2013-02-28 | 2019-04-03 | United Technologies Corporation | Contoured blade outer air seal for a gas turbine engine |
WO2014158236A1 (en) * | 2013-03-12 | 2014-10-02 | United Technologies Corporation | Cantilever stator with vortex initiation feature |
US10465716B2 (en) * | 2014-08-08 | 2019-11-05 | Pratt & Whitney Canada Corp. | Compressor casing |
US10066640B2 (en) * | 2015-02-10 | 2018-09-04 | United Technologies Corporation | Optimized circumferential groove casing treatment for axial compressors |
JP6276209B2 (ja) * | 2015-02-20 | 2018-02-07 | 三菱日立パワーシステムズ株式会社 | タービン用シール装置及びタービン、並びにシール装置用の薄板 |
US10107307B2 (en) | 2015-04-14 | 2018-10-23 | Pratt & Whitney Canada Corp. | Gas turbine engine rotor casing treatment |
US10487847B2 (en) * | 2016-01-19 | 2019-11-26 | Pratt & Whitney Canada Corp. | Gas turbine engine blade casing |
US10648484B2 (en) | 2017-02-14 | 2020-05-12 | Honeywell International Inc. | Grooved shroud casing treatment for high pressure compressor in a turbine engine |
CN108506249B (zh) * | 2018-04-02 | 2020-03-10 | 华能国际电力股份有限公司 | 一种用于轴流压气机的槽类端壁处理方法 |
US11015465B2 (en) | 2019-03-25 | 2021-05-25 | Honeywell International Inc. | Compressor section of gas turbine engine including shroud with serrated casing treatment |
CN115095548B (zh) * | 2022-07-27 | 2022-11-22 | 中国航发沈阳发动机研究所 | 一种航空发动机压气机机匣内转子叶片抑振结构 |
Family Cites Families (23)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1482031A (en) * | 1923-01-18 | 1924-01-29 | Said Parsons | Packing for rotating bodies |
GB225936A (en) * | 1923-09-12 | 1924-12-12 | Karl Baumann | Improvements in labyrinth gland packing |
AT121156B (de) * | 1928-07-09 | 1931-02-10 | Erste Bruenner Maschinen Fab | Labyrinthdichtung für sich drehende Wellen, insbesondere von Dampfturbinen. |
GB615961A (en) * | 1945-06-06 | 1949-01-13 | Olaer Patent Co | Improvements in aircraft landing gears |
FR1218301A (fr) * | 1958-03-07 | 1960-05-10 | Maschf Augsburg Nuernberg Ag | Amélioration de l'étanchéité du joint des aubages mobiles de turbo-machines |
GB874010A (en) * | 1958-06-10 | 1961-08-02 | Woodhead Monroe Ltd | Improvements in or relating to sealing devices |
US3119624A (en) * | 1960-11-18 | 1964-01-28 | Duriron Co | Lip seals |
US3144256A (en) * | 1962-08-06 | 1964-08-11 | Clarence E Wright | Free piston seal |
FR1348186A (fr) * | 1963-02-19 | 1964-01-04 | Hélice carénée | |
US3392910A (en) * | 1963-08-23 | 1968-07-16 | Atomic Energy Commission Usa | Seal |
US3414272A (en) * | 1966-03-11 | 1968-12-03 | John B. Rogers Jr. | Piston rings |
NL6713596A (ja) * | 1967-10-06 | 1969-04-09 | ||
US4055041A (en) * | 1974-11-08 | 1977-10-25 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Integrated gas turbine engine-nacelle |
GB1518293A (en) * | 1975-09-25 | 1978-07-19 | Rolls Royce | Axial flow compressors particularly for gas turbine engines |
US4022479A (en) * | 1976-01-02 | 1977-05-10 | Orlowski David C | Sealing rings |
GB2017228B (en) * | 1977-07-14 | 1982-05-06 | Pratt & Witney Aircraft Of Can | Shroud for a turbine rotor |
FR2406074A1 (fr) * | 1977-10-11 | 1979-05-11 | Snecma | Dispositif de securite pour machine tournante axiale |
US4175752A (en) * | 1977-11-25 | 1979-11-27 | Inpro, Inc. | Two stage labyrinth pattern inclusion device |
US4239452A (en) * | 1978-06-26 | 1980-12-16 | United Technologies Corporation | Blade tip shroud for a compression stage of a gas turbine engine |
FR2437544A1 (fr) * | 1978-09-27 | 1980-04-25 | Snecma | Perfectionnements aux joints a labyrinthe |
JPS5560699A (en) * | 1978-10-24 | 1980-05-07 | Gerry U K | Rotary power converter with fluid as medium |
NL7811164A (nl) * | 1978-11-10 | 1980-05-13 | Ihc Holland Nv | Afdichting van een as. |
CA1158563A (en) * | 1981-01-27 | 1983-12-13 | Ulo Okapuu | Circumferentially grooved shroud liner |
-
1984
- 1984-02-01 FR FR8401530A patent/FR2558900B1/fr not_active Expired
-
1985
- 1985-01-24 DE DE8585400112T patent/DE3564147D1/de not_active Expired
- 1985-01-24 EP EP19850400112 patent/EP0151071B1/fr not_active Expired
- 1985-01-29 JP JP60015260A patent/JPS60243400A/ja active Granted
-
1987
- 1987-03-13 US US07/024,864 patent/US4767266A/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
EP0151071A3 (en) | 1985-09-25 |
FR2558900A1 (fr) | 1985-08-02 |
JPH0250320B2 (ja) | 1990-11-01 |
FR2558900B1 (fr) | 1988-05-27 |
DE3564147D1 (en) | 1988-09-08 |
US4767266A (en) | 1988-08-30 |
JPS60243400A (ja) | 1985-12-03 |
EP0151071A2 (fr) | 1985-08-07 |
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