US20090155073A1 - Sealing the fastening of a bearing support in a turbomachine - Google Patents
Sealing the fastening of a bearing support in a turbomachine Download PDFInfo
- Publication number
- US20090155073A1 US20090155073A1 US12/329,925 US32992508A US2009155073A1 US 20090155073 A1 US20090155073 A1 US 20090155073A1 US 32992508 A US32992508 A US 32992508A US 2009155073 A1 US2009155073 A1 US 2009155073A1
- Authority
- US
- United States
- Prior art keywords
- support
- cover
- bolts
- annular
- downstream
- 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.)
- Abandoned
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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
- F01D25/16—Arrangement of bearings; Supporting or mounting bearings in casings
- F01D25/162—Bearing supports
-
- 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
-
- 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
- F02C7/28—Arrangement of seals
Definitions
- a bypass turbomachine includes a fan arranged at its upstream end and driven in rotation by a shaft that is guided by upstream and downstream bearings carried by respective first and second annular supports.
- the upstream bearing is carried by the upstream end of the first support whose own downstream end includes a plurality of orifices distributed around its circumference, thereby enabling it to be fastened by bolting to a radially outer portion of the second support, which is in turn fastened by bolting to an intermediate casing situated downstream from a low-pressure compressor.
- the downstream end of the first support includes an annular rim formed with a plurality of notches that receive the upstream portions of bolts for fastening the first support to the second support. These notches open out into cavities machined in the rim of the support for receiving the heads of the bolts. Washers are engaged on the bolts to form continuous bearing surfaces for the heads of the bolts against the rim of the support.
- Sealing against the lubricating oil for the upstream and downstream bearing is provided by means of a first sealing ring situated radially outside the fastener bolt in an annular groove in the upstream radial face of the second support that comes into contact with the downstream end of the first support, and by means of a second sealing ring placed in an annular groove between facing cylindrical surfaces of the second support and of the intermediate casing.
- the fastener bolts used are fuse bolts.
- the resulting unbalance gives rise at the first support to a traction force on the fastener bolts, which are designed to break when the applied load exceeds a predetermined value.
- locating these bolts inside the first support leads to bolt debris being ejected into the inter-bearing enclosure, and that can damage the upstream and downstream bearings and other parts located therein such as enclosure de-oilers, oil nozzles, etc.
- the bolts come into contact with the lubricating oil for the upstream and downstream bearings and therefore need to comply with strict cleanliness criteria.
- a particular object of the present invention is to avoid those drawbacks of the prior art in a manner that is simple, effective, and inexpensive.
- the invention provides a turbomachine including a shaft guided in an upstream bearing and a downstream bearing, the upstream bearing carried by a first annular support that is fastened by bolts to a casing via a second annular support that carries the downstream bearing, wherein the ends of the bolts for fastening the first support to the second support are covered by an annular cover sealingly fastened to the second support or to the casing.
- annular cover makes it possible to use a single part to cover all of the ends of the bolts and, in the event of a blade being lost, serves to avoid debris from the bolts escaping into the inter-bearing enclosure.
- the bolts for fastening the first support are on the outside of the support, thus making it possible to avoid solid particles present on the fuse bolts penetrating into the inter-bearing enclosure and polluting the lubricating oil for the upstream and downstream bearings. Placing the bolts outside relative to the first support also makes it possible, in the event of a blade being lost, to keep the debris of the upstream portions of the fuse bolts outside the inter-bearing enclosure.
- the downstream end of the first bearing support is fastened to the second support more simply, and it is no longer necessary to make use of washers since the heads of the bolts can bear around their entire circumference. It is also simple to fabricate the first support since this part no longer presents a complex shape at its downstream end, as it does in the prior art.
- the annular cover is of U-shaped section comprising two parallel walls sealingly engaged against a cylindrical wall of the second support and inside a cylindrical wall of the casing.
- a sealing ring is mounted in an annular groove in an upstream radial face of the second support or in a corresponding downstream radial face of the first support, and sealing rings are mounted in annular grooves in the walls of the cover or in cylindrical walls of the second support and of the cover, thereby enabling a small number of sealing rings to seal the connection between the first support and the second support and preventing oil from escaping from the inter-bearing enclosure via the bolts.
- the cover is preferably made of a material having a coefficient of expansion similar to the coefficients of expansion of the second support and of the casing.
- the cover is held in position covering the ends of the bolts by means of a downstream cylindrical rim of the cover that is fastened by bolts to a downstream cylindrical rim of the second support.
- the cover may also be fastened directly to the casing by means of bolts.
- the invention also provides an annular sealing cover for use in a turbomachine as described above, wherein the cover presents a U-shaped section with two parallel cylindrical walls that are respectively a radially inner wall and a radially outer wall, with at least the radially outer wall including an outer annular groove for receiving a sealing ring.
- the cover includes a cylindrical rim extending its radially inner cylindrical wall in the opposite direction and including regularly distributed orifices for passing fastener means.
- the cover may be made of a composite material or of a metal, e.g. titanium.
- FIG. 1 is a partial schematic half-view in axial section of a turbomachine with a prior art bearing support
- FIG. 2 is a partial perspective view seen from downstream showing the upstream bearing support of FIG. 1 ;
- FIG. 3 is a partial schematic half-view in axial section of a turbomachine with a bearing support according to the invention.
- FIG. 4 is a view on a larger scale showing a detail of FIG. 3 marked by a box of chain-dotted outline.
- FIG. 1 showing an upstream portion of a prior art turbomachine that includes a fan wheel 10 driven in rotation about the axis 12 of the turbomachine by a shaft 14 having its upstream end fastened by bolts 16 to a frustoconical wall 18 that is secured to the fan wheel 10 .
- the shaft 14 is fastened to the end of a shaft 20 of a low-pressure turbine (not shown).
- the fan wheel 10 is secured to the rotor 22 of a low-pressure compressor that is associated with an intermediate casing 24 .
- the shaft 14 is supported and guided by upstream and downstream bearings 26 and 28 .
- the upstream bearing 26 is carried by the upstream end of a first annular support 30 having its downstream end fastened by fuse bolts 32 to a radially outer portion of a second annular support 34 that carries the downstream bearing 28 at its radially inner end.
- the second support 34 is fastened by bolts 36 to a flange 38 of the intermediate casing 24 .
- the downstream end of the first support 30 has notches 40 facing radially towards the inside of the turbomachine, which notches are distributed around the entire circumference of an annular rim of the first support 30 in order to receive the upstream ends of the fuse bolts 32 ( FIG. 2 ).
- Each notch 40 opens out into a cavity 42 in which there is received the head 44 of a fuse bolt 32 .
- the heads 44 of the fuse bolts 32 come into abutment against the ends of the notches 40 when the nuts 48 are tightened onto the fuse bolts 32 .
- Washers 46 are interposed between the heads 44 of the bolts 32 and the notches 40 so as to enable the heads 44 of the bolts 32 to bear continuously all around their circumference.
- Each fuse bolt 32 presents a narrowing in its portion situated in the notch 40 , thereby enabling the corresponding bolt 32 to break at that location when the load that is applied thereto is too great.
- the appearance of unbalance on the fan shaft 14 can lead to high levels of traction force on the fuse bolts 32 .
- Decoupling the first and second supports 30 and 34 makes it possible to accommodate the unbalance and to limit the transmission of forces to the intermediate casing 24 and to the turbomachine as a whole.
- the first support 50 comprises a frustoconical wall 56 of section that tapers going upstream, carrying at its upstream end the upstream bearing 26 , and connected at its downstream end to a cylindrical wall 58 with its downstream end including an annular rim 60 that extends radially outwards.
- Bolt-passing orifices are formed in the annular rim 60 in alignment with corresponding orifices in the radially outer portion of the second support 52 for receiving the fuse bolts 32 .
- the upstream end of each fuse bolt 32 has a head 44 bearing axially over its entire circumference against the upstream face of the annular rim 60 , its downstream end receiving a nut 62 that is tightened against the radially outer portion of the second support 52 .
- annular cover 54 that presents a U-shaped cross-section and that comprises two parallel walls, respectively a radially inner wall 64 and a radially outer wall 66 , the inner wall 64 being connected to a cylindrical rim 68 that extends downstream and that includes orifices for passing bolts that are regularly distributed around the axis 12 of the turbomachine.
- the cover 54 covers the downstream end of the fuse bolts 32 and its radially inner 64 and outer 66 walls are sealingly engaged against a cylindrical wall 70 of the second support 52 and in a cylindrical wall 72 of the flange 38 of the intermediate casing 24 .
- the cover 54 is held in position by bolts 73 inserted in the orifices through the downstream cylindrical rim 68 of the cover 54 and through corresponding orifices in a cylindrical rim 74 of the second support 52 .
- the radially outer wall 66 of the cover 54 and the cylindrical wall 70 of the second support 52 include respective annular grooves facing radially outwards and receiving sealing rings 76 and 78 . These two sealing rings 76 and 78 prevent lubricating oil from the upstream 26 and downstream 28 bearings escaping via the orifices through which the fuse bolts 32 pass and via the contact zones between the second support 52 and the intermediate casing 24 .
- a third sealing ring 80 is mounted in an annular groove in an upstream radial face of the second support 52 , this upstream face being in contact with a radial downstream face of the first support 50 .
- This sealing ring 80 lies radially inside the fuse bolts 32 so as to prevent oil from escaping via the bolt-passing orifices in the rim 60 .
- the annular cover 54 serves to contain the debris of the downstream ends of the fuse bolts 32 , while fastening the bolts 32 radially outside the first support 50 serves to avoid the debris of the heads 44 of the bolts 32 penetrating into the inter-bearing enclosure and damaging the parts situated therein.
- the cover 54 also serves to seal the downstream end of the fuse bolts 32 and to simplify fabrication of the first support 50 since it is no longer necessary to make notches and cavities in a rim of said support.
- the radially outer end of the second support 52 is fastened to the intermediate casing 24 by means of bolts 36 screwed into a flange 38 of the intermediate casing 24 .
- the cover 54 is made of a material that presents a coefficient of thermal expansion close to those of the materials of the second support 52 and of the intermediate casing 24 so as to guarantee good sealing by the sealing rings 76 , 78 , and 80 at the temperatures to which these various parts are subjected.
- the cover 54 may be made of composite material or of metal, such as titanium, for example.
- the cover 54 may include a downstream radial annular rim fastened by bolts to a downstream annular rim of the second support 52 or of the flange 38 of the intermediate casing 24 .
Abstract
A turbomachine including a shaft guided in an upstream bearing and a downstream bearing, the upstream bearing being carried by a first annular support that is fastened by bolts to a casing via a second annular support that carries the downstream bearing, wherein the ends of the fastener bolts are covered by an annular cover sealingly fastened to the second support or to the casing.
Description
- A bypass turbomachine includes a fan arranged at its upstream end and driven in rotation by a shaft that is guided by upstream and downstream bearings carried by respective first and second annular supports. The upstream bearing is carried by the upstream end of the first support whose own downstream end includes a plurality of orifices distributed around its circumference, thereby enabling it to be fastened by bolting to a radially outer portion of the second support, which is in turn fastened by bolting to an intermediate casing situated downstream from a low-pressure compressor.
- The downstream end of the first support includes an annular rim formed with a plurality of notches that receive the upstream portions of bolts for fastening the first support to the second support. These notches open out into cavities machined in the rim of the support for receiving the heads of the bolts. Washers are engaged on the bolts to form continuous bearing surfaces for the heads of the bolts against the rim of the support.
- Sealing against the lubricating oil for the upstream and downstream bearing is provided by means of a first sealing ring situated radially outside the fastener bolt in an annular groove in the upstream radial face of the second support that comes into contact with the downstream end of the first support, and by means of a second sealing ring placed in an annular groove between facing cylindrical surfaces of the second support and of the intermediate casing.
- Nevertheless, that type of fastening presents several drawbacks. Firstly, making cavities in the downstream rim of the first support is lengthy and difficult. Furthermore, the bolts mounted in the notches of the first support are not retained until the second support is in place, thereby complicating the assembly process.
- The fastener bolts used are fuse bolts. Thus, in the event of a blade being lost, the resulting unbalance gives rise at the first support to a traction force on the fastener bolts, which are designed to break when the applied load exceeds a predetermined value. Nevertheless, locating these bolts inside the first support leads to bolt debris being ejected into the inter-bearing enclosure, and that can damage the upstream and downstream bearings and other parts located therein such as enclosure de-oilers, oil nozzles, etc. In addition, the bolts come into contact with the lubricating oil for the upstream and downstream bearings and therefore need to comply with strict cleanliness criteria.
- A particular object of the present invention is to avoid those drawbacks of the prior art in a manner that is simple, effective, and inexpensive.
- To this end, the invention provides a turbomachine including a shaft guided in an upstream bearing and a downstream bearing, the upstream bearing carried by a first annular support that is fastened by bolts to a casing via a second annular support that carries the downstream bearing, wherein the ends of the bolts for fastening the first support to the second support are covered by an annular cover sealingly fastened to the second support or to the casing.
- The use of an annular cover makes it possible to use a single part to cover all of the ends of the bolts and, in the event of a blade being lost, serves to avoid debris from the bolts escaping into the inter-bearing enclosure.
- Advantageously, the bolts for fastening the first support are on the outside of the support, thus making it possible to avoid solid particles present on the fuse bolts penetrating into the inter-bearing enclosure and polluting the lubricating oil for the upstream and downstream bearings. Placing the bolts outside relative to the first support also makes it possible, in the event of a blade being lost, to keep the debris of the upstream portions of the fuse bolts outside the inter-bearing enclosure.
- The downstream end of the first bearing support is fastened to the second support more simply, and it is no longer necessary to make use of washers since the heads of the bolts can bear around their entire circumference. It is also simple to fabricate the first support since this part no longer presents a complex shape at its downstream end, as it does in the prior art.
- Advantageously, the annular cover is of U-shaped section comprising two parallel walls sealingly engaged against a cylindrical wall of the second support and inside a cylindrical wall of the casing.
- According to another feature of the invention, a sealing ring is mounted in an annular groove in an upstream radial face of the second support or in a corresponding downstream radial face of the first support, and sealing rings are mounted in annular grooves in the walls of the cover or in cylindrical walls of the second support and of the cover, thereby enabling a small number of sealing rings to seal the connection between the first support and the second support and preventing oil from escaping from the inter-bearing enclosure via the bolts.
- In order to guarantee good sealing in operation, the cover is preferably made of a material having a coefficient of expansion similar to the coefficients of expansion of the second support and of the casing.
- The cover is held in position covering the ends of the bolts by means of a downstream cylindrical rim of the cover that is fastened by bolts to a downstream cylindrical rim of the second support. The cover may also be fastened directly to the casing by means of bolts.
- The invention also provides an annular sealing cover for use in a turbomachine as described above, wherein the cover presents a U-shaped section with two parallel cylindrical walls that are respectively a radially inner wall and a radially outer wall, with at least the radially outer wall including an outer annular groove for receiving a sealing ring.
- According to another feature of the invention, the cover includes a cylindrical rim extending its radially inner cylindrical wall in the opposite direction and including regularly distributed orifices for passing fastener means.
- The cover may be made of a composite material or of a metal, e.g. titanium.
- The invention can be better understood and other details, advantages, and characteristics of the invention appear on reading the following description made by way of non-limiting example, with reference to the accompanying drawings, in which:
-
FIG. 1 is a partial schematic half-view in axial section of a turbomachine with a prior art bearing support; -
FIG. 2 is a partial perspective view seen from downstream showing the upstream bearing support ofFIG. 1 ; -
FIG. 3 is a partial schematic half-view in axial section of a turbomachine with a bearing support according to the invention; and -
FIG. 4 is a view on a larger scale showing a detail ofFIG. 3 marked by a box of chain-dotted outline. - Reference is made initially to
FIG. 1 showing an upstream portion of a prior art turbomachine that includes afan wheel 10 driven in rotation about theaxis 12 of the turbomachine by ashaft 14 having its upstream end fastened bybolts 16 to afrustoconical wall 18 that is secured to thefan wheel 10. Theshaft 14 is fastened to the end of ashaft 20 of a low-pressure turbine (not shown). Thefan wheel 10 is secured to therotor 22 of a low-pressure compressor that is associated with anintermediate casing 24. - The
shaft 14 is supported and guided by upstream anddownstream bearings annular support 30 having its downstream end fastened byfuse bolts 32 to a radially outer portion of a secondannular support 34 that carries the downstream bearing 28 at its radially inner end. Thesecond support 34 is fastened bybolts 36 to aflange 38 of theintermediate casing 24. - The downstream end of the
first support 30 hasnotches 40 facing radially towards the inside of the turbomachine, which notches are distributed around the entire circumference of an annular rim of thefirst support 30 in order to receive the upstream ends of the fuse bolts 32 (FIG. 2 ). Eachnotch 40 opens out into acavity 42 in which there is received thehead 44 of afuse bolt 32. Theheads 44 of thefuse bolts 32 come into abutment against the ends of thenotches 40 when thenuts 48 are tightened onto thefuse bolts 32.Washers 46 are interposed between theheads 44 of thebolts 32 and thenotches 40 so as to enable theheads 44 of thebolts 32 to bear continuously all around their circumference. - Each
fuse bolt 32 presents a narrowing in its portion situated in thenotch 40, thereby enabling thecorresponding bolt 32 to break at that location when the load that is applied thereto is too great. In the event of a blade being lost, the appearance of unbalance on thefan shaft 14 can lead to high levels of traction force on thefuse bolts 32. Decoupling the first andsecond supports intermediate casing 24 and to the turbomachine as a whole. - As mentioned above, this technique for fastening the first and second supports 30 and 34 presents several drawbacks.
- According to the invention, and as shown in
FIG. 3 , these drawbacks are avoided by the fact that the downstream of thefirst support 50 is fastened to the radially outer portion of thesecond support 52 byfuse bolts 32 that are radially at the outside of thefirst support 50, with a leak-tight connection being provided in a manner that is simple and inexpensive. - The
first support 50 comprises afrustoconical wall 56 of section that tapers going upstream, carrying at its upstream end the upstream bearing 26, and connected at its downstream end to acylindrical wall 58 with its downstream end including anannular rim 60 that extends radially outwards. Bolt-passing orifices are formed in theannular rim 60 in alignment with corresponding orifices in the radially outer portion of thesecond support 52 for receiving thefuse bolts 32. The upstream end of eachfuse bolt 32 has ahead 44 bearing axially over its entire circumference against the upstream face of theannular rim 60, its downstream end receiving anut 62 that is tightened against the radially outer portion of thesecond support 52. - The downstream ends of the
bolts 32 and of thenuts 62 are covered by anannular cover 54 that presents a U-shaped cross-section and that comprises two parallel walls, respectively a radiallyinner wall 64 and a radiallyouter wall 66, theinner wall 64 being connected to acylindrical rim 68 that extends downstream and that includes orifices for passing bolts that are regularly distributed around theaxis 12 of the turbomachine. - The
cover 54 covers the downstream end of thefuse bolts 32 and its radially inner 64 and outer 66 walls are sealingly engaged against acylindrical wall 70 of thesecond support 52 and in acylindrical wall 72 of theflange 38 of theintermediate casing 24. Thecover 54 is held in position bybolts 73 inserted in the orifices through the downstreamcylindrical rim 68 of thecover 54 and through corresponding orifices in acylindrical rim 74 of thesecond support 52. - The radially
outer wall 66 of thecover 54 and thecylindrical wall 70 of thesecond support 52 include respective annular grooves facing radially outwards and receivingsealing rings sealing rings second support 52 and theintermediate casing 24. - A
third sealing ring 80 is mounted in an annular groove in an upstream radial face of thesecond support 52, this upstream face being in contact with a radial downstream face of thefirst support 50. This sealingring 80 lies radially inside thefuse bolts 32 so as to prevent oil from escaping via the bolt-passing orifices in therim 60. - In the event of the first and second supports 50 and 52 being decoupled, the
annular cover 54 serves to contain the debris of the downstream ends of thefuse bolts 32, while fastening thebolts 32 radially outside thefirst support 50 serves to avoid the debris of theheads 44 of thebolts 32 penetrating into the inter-bearing enclosure and damaging the parts situated therein. - The
cover 54 also serves to seal the downstream end of thefuse bolts 32 and to simplify fabrication of thefirst support 50 since it is no longer necessary to make notches and cavities in a rim of said support. - It is no longer essential to use washers since the
head 44 of eachfuse bolt 32 bears around its entire circumference against the upstream face of theannular rim 60. - The radially outer end of the
second support 52 is fastened to theintermediate casing 24 by means ofbolts 36 screwed into aflange 38 of theintermediate casing 24. - Advantageously, the
cover 54 is made of a material that presents a coefficient of thermal expansion close to those of the materials of thesecond support 52 and of theintermediate casing 24 so as to guarantee good sealing by the sealing rings 76, 78, and 80 at the temperatures to which these various parts are subjected. - The
cover 54 may be made of composite material or of metal, such as titanium, for example. - In a variant of the invention, the
cover 54 may include a downstream radial annular rim fastened by bolts to a downstream annular rim of thesecond support 52 or of theflange 38 of theintermediate casing 24.
Claims (12)
1. A turbomachine including a shaft guided in an upstream bearing and a downstream bearing, the upstream bearing being carried by a first annular support that is fastened by bolts to a casing via a second annular support that carries the downstream bearing, wherein the ends of the bolts for fastening the first support to the second support are covered by an annular cover sealingly fastened to the second support or to the casing.
2. A turbomachine according to claim 1 , wherein the bolts for fastening the first support are on the outside of the support.
3. A turbomachine according to claim 1 , wherein the cover is of U-shaped section comprising two parallel walls sealingly engaged against a cylindrical wall of the second support and inside a cylindrical wall of the casing.
4. A turbomachine according to claim 3 , wherein annular sealing rings are mounted in annular grooves in the walls of the cover or in the cylindrical walls of the second support and of the cover.
5. A turbomachine according to claim 1 , wherein the ends of the bolts situated inside the cover carry nuts.
6. A turbomachine according to claim 1 , wherein a sealing ring is mounted in an annular groove in an upstream radial face of the second support or in a corresponding downstream radial face of the first support.
7. A turbomachine according to claim 1 , wherein the cover is made of a material having a coefficient of expansion similar to the coefficients of expansion of the second support and of the casing.
8. A turbomachine according to claim 1 , wherein the cover has a downstream cylindrical rim fastened by bolts to a downstream cylindrical rim of the second support.
9. A turbomachine according to claim 1 , wherein the cover is fastened by bolts to the casing.
10. An annular sealing cover for use in a turbomachine according to claim 1 , wherein the cover presents a U-shaped section with two parallel cylindrical walls that are respectively a radially inner wall and a radially outer wall, with at least the radially outer wall including an outer annular groove for receiving a sealing ring.
11. A cover according to claim 10 , made of composite material or of metal, such as titanium, for example.
12. A cover according to claim 10 , including a cylindrical rim extending its radially inner cylindrical wall in the opposite direction and including regularly distributed orifices for passing fastener means.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0708706 | 2007-12-14 | ||
FR0708706A FR2925123A1 (en) | 2007-12-14 | 2007-12-14 | SEALING OF BEARING SUPPORT FIXATION IN A TURBOMACHINE |
Publications (1)
Publication Number | Publication Date |
---|---|
US20090155073A1 true US20090155073A1 (en) | 2009-06-18 |
Family
ID=39743779
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/329,925 Abandoned US20090155073A1 (en) | 2007-12-14 | 2008-12-08 | Sealing the fastening of a bearing support in a turbomachine |
Country Status (6)
Country | Link |
---|---|
US (1) | US20090155073A1 (en) |
EP (1) | EP2071141B1 (en) |
JP (1) | JP2009144715A (en) |
CA (1) | CA2646976A1 (en) |
FR (1) | FR2925123A1 (en) |
RU (1) | RU2008149140A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2397710A3 (en) * | 2010-06-15 | 2013-04-03 | Rolls-Royce Corporation | Bearing support |
US20130305684A1 (en) * | 2012-05-21 | 2013-11-21 | Jacob Peter Mastro | Debris discourager |
EP2775102A3 (en) * | 2013-03-08 | 2018-05-23 | General Electric Company | Device and method for preventing leakage of air between multiple turbine components |
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Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2873810B2 (en) | 2013-11-18 | 2020-07-01 | Safran Aero Boosters SA | Annular cover for defining a turbomachine lubrication chamber |
US10247106B2 (en) * | 2016-06-15 | 2019-04-02 | General Electric Company | Method and system for rotating air seal with integral flexible heat shield |
CN107121289B (en) * | 2017-04-21 | 2019-04-23 | 中国航发沈阳发动机研究所 | A kind of bearing bore of aero-engine high supercharging pressure level Fan Rig obturages system |
JP7032279B2 (en) * | 2018-10-04 | 2022-03-08 | 本田技研工業株式会社 | Gas turbine engine |
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US6240719B1 (en) * | 1998-12-09 | 2001-06-05 | General Electric Company | Fan decoupler system for a gas turbine engine |
EP1314854A1 (en) * | 2001-11-23 | 2003-05-28 | Techspace Aero S.A. | De-coupling device for an aircraft motor |
FR2845126B1 (en) * | 2002-09-26 | 2004-12-03 | Snecma Moteurs | TRACTION COUPLER DEVICE |
FR2878289A1 (en) * | 2004-11-19 | 2006-05-26 | Snecma Moteurs Sa | TURBOMACHINE WITH A DECOUPLING DEVICE COMMON TO THE FIRST AND SECOND BEARINGS OF ITS DRIVE SHAFT |
-
2007
- 2007-12-14 FR FR0708706A patent/FR2925123A1/en not_active Withdrawn
-
2008
- 2008-11-12 EP EP08168912A patent/EP2071141B1/en active Active
- 2008-12-08 US US12/329,925 patent/US20090155073A1/en not_active Abandoned
- 2008-12-10 JP JP2008314057A patent/JP2009144715A/en not_active Withdrawn
- 2008-12-10 CA CA002646976A patent/CA2646976A1/en not_active Abandoned
- 2008-12-12 RU RU2008149140/06A patent/RU2008149140A/en not_active Application Discontinuation
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US4883407A (en) * | 1987-12-16 | 1989-11-28 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" | Screwed attachment of a body of revolution to an annular flange in a turbine engine |
JP2005240799A (en) * | 2004-02-06 | 2005-09-08 | Snecma Moteurs | Turbojet having fan mounted on drive shaft supported by first and second bearing |
US7322180B2 (en) * | 2004-02-06 | 2008-01-29 | Snecma Moteurs | Turbo-jet engine with fan integral with a drive shaft supported by first and second bearings |
US7322181B2 (en) * | 2004-02-06 | 2008-01-29 | Snecma Moteurs | Turbofan engine with the fan fixed to a drive shaft supported by a first and a second bearing |
US7340882B2 (en) * | 2004-06-11 | 2008-03-11 | Snecma Moteurs | Turbomachine with means for axial retention of the rotor |
US20070278874A1 (en) * | 2006-05-19 | 2007-12-06 | Hispano Suiza | Airplane engine accessory box |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2397710A3 (en) * | 2010-06-15 | 2013-04-03 | Rolls-Royce Corporation | Bearing support |
US8573922B2 (en) | 2010-06-15 | 2013-11-05 | Rolls-Royce Corporation | Bearing support |
US20130305684A1 (en) * | 2012-05-21 | 2013-11-21 | Jacob Peter Mastro | Debris discourager |
US9309775B2 (en) * | 2012-05-21 | 2016-04-12 | United Technologies Corporation | Rotational debris discourager for gas turbine engine bearing |
EP2775102A3 (en) * | 2013-03-08 | 2018-05-23 | General Electric Company | Device and method for preventing leakage of air between multiple turbine components |
Also Published As
Publication number | Publication date |
---|---|
EP2071141A1 (en) | 2009-06-17 |
RU2008149140A (en) | 2010-06-20 |
EP2071141B1 (en) | 2011-06-22 |
JP2009144715A (en) | 2009-07-02 |
FR2925123A1 (en) | 2009-06-19 |
CA2646976A1 (en) | 2009-06-14 |
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Owner name: SNECMA, FRANCE Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:SERVANT, REGIS EUGENE HENRI;REEL/FRAME:021940/0098 Effective date: 20081030 |
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