EP0922837B1 - Boitier pour une soufflante - Google Patents
Boitier pour une soufflante Download PDFInfo
- Publication number
- EP0922837B1 EP0922837B1 EP19980309221 EP98309221A EP0922837B1 EP 0922837 B1 EP0922837 B1 EP 0922837B1 EP 19980309221 EP19980309221 EP 19980309221 EP 98309221 A EP98309221 A EP 98309221A EP 0922837 B1 EP0922837 B1 EP 0922837B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fan
- case
- fan case
- liner
- rotor
- 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 - Lifetime
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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
Definitions
- the present invention relates to gas turbine engines, and more particularly, to providing a hardened liner in the fan case of the engine to minimize damage to the fan case in the event of a fan blade loss.
- a gas turbine engine such as a turbofan engine for an aircraft, includes a fan section, a compression section, a combustion section, and a turbine section. An axis of the engine is centrally disposed within the engine, and extends longitudinally through these sections. A primary flow path for working medium gases extends axially through the engine. A secondary flow path for working medium gases extends parallel to and radially outward of the primary flow path.
- the fan draws air into the engine.
- the fan raises the pressure of the air drawn along the secondary flow path, thus producing useful thrust.
- the air drawn along the primary flow path into the compressor section is compressed.
- the compressed air is channelled to the combustor section, where fuel is added to the compressed air, and the air-fuel mixture is burned.
- the products of combustion are discharged to the turbine section.
- the turbine section extracts work from these products to power the fan and compressor. Any energy from the products of combustion not needed to drive the fan and compressor contributes to useful thrust.
- the fan section includes a rotor assembly and a stator assembly.
- the rotor assembly of the fan includes a rotor disk and a plurality of outwardly extending rotor blades.
- Each rotor blade includes an airfoil portion, a root portion, and a tip portion.
- the airfoil portion extends through the flow path and interacts with the working medium gases to transfer energy between the rotor blade and working medium gases.
- the stator assembly includes a fan containment case assembly, which circumscribes the rotor assembly in close proximity to the tips of the rotor blades.
- the fan containment case assembly includes a fan case which provides a support structure, a plurality of fabric wraps disposed radially outwardly of the fan case, a plurality of circumferentially adjacent acoustic panels and a plurality of circumferentially adjacent rub strips disposed radially inwardly of the fan case.
- Conventional fan cases are typically a solid metal casing which forms a rigid structure to support the fabric wraps.
- the plurality of rub strips are formed from a relatively compliant material. In the event that the tip of a fan blade makes contact with the rub strips, the compliance of the rub strips minimizes the risks of damage to the fan blade.
- the first one is characterized as a performance clearance and is defined as the clearance between the blade tips and the soft rub strip in the inner surface of the fan case.
- the second clearance is characterized as an effective structural clearance and is defined as the clearance between the blade tips and a hard metallic surface in the fan case.
- the present invention is concerned with this structural clearance, as opposed to the performance clearance.
- Severe rotor imbalance can occur in an engine, particularly after a fan blade breaks off from the rotor assembly.
- One cause of fan blade loss is impact with foreign objects, such as birds, hailstones or other objects which, on occasion, are ingested into the engine.
- the detached fan blade is thrown outwardly and passes through the fan case, but is typically caught by the fabric wraps in the fan containment case assembly.
- Blade loss produces an imbalance in the rotor and causes the rotor shaft to deflect radially outwardly. Deflection of the rotor away from its longitudinal axis may also lead to additional damage to the rotor assembly. The more the rotor deflects, the greater is the radial load on the rotor bearing supports.
- the fan case structure stops the deflection of the rotor assembly.
- the damage to the rotor assembly is reduced by decreasing the fan tip-to-case clearance as the shaft deflection is limited by the proximal portion of the fan case assembly.
- Minimizing the amount of radial deflection of the shaft minimizes the likelihood of damage occurring in the shaft, the rotor bearings and the bearing support structures.
- the deflection of the shaft was restrained by the fan blades embedding themselves in the fan case.
- the fan blades rapidly cut away and destroy the fan case because the blades are usually of a harder material than the fan case.
- the fan blades continue to rotate, they couple with the static fan case structure and transmit the kinetic energy of the rotor shaft to the case, causing twisting of and damage to the case.
- Due to the coupling of the rotor shaft with the fan case high torque loads are transmitted to the fan case. This torque loading of the fan case during a fan blade loss event, results in tremendous loads being imposed upon the related engine mounts and engine case structure.
- US-A-5,403,148 discloses a gas turbiine engine having the faetures of the preamble of claim 1.
- a fan case in a gas turbine engine includes a liner of hardened material attached thereto wherein during a fan blade loss condition, the blade tips skid on the hardened liner and reduce the destructive cutting away of the fan case.
- This liner of hardened material provides a skid-surface for the blades to circumferentially glide on and precludes or reduces embedding of the blades in the fan case and thus minimizes torque loading of the fan case.
- the fan case structure of the present invention limits the deflection of the rotor shaft during a fan blade loss event.
- the liner of hardened material comprises a plurality of shingles.
- a primary advantage of the present invention is the minimization of damage to the fan case, thus resulting in a durable fan case in the event of a fan blade loss.
- the hardened fan case liner of the present invention reduces the destructive cutting away of the fan case by the fan blades.
- a further advantage of the fan case of the present invention is its ability to provide an appropriate restraining structure to the deflection of the rotor shaft during a fan blade loss event.
- the hardened liner reduces frictional forces and therefore, the torque transmitted from the rotor to the engine cases.
- Another advantage is the ease and cost of manufacturing and incorporating into the fan case the liner of the present invention. The simplicity of the structure of the liner and the use of economic materials, allows for cost effective manufacturing processes. Further, fan cases of the prior art can be retrofitted to include the present invention in a cost effective manner.
- an axial flow, turbofan gas turbine engine 10 comprises a fan section 14, a compressor section 16, a combustor section 18 and a turbine section 20.
- An axis of the engine Ar is centrally disposed within the engine and extends longitudinally through these sections.
- a primary flow path 22 for working medium gases extends longitudinally along the axis Ar.
- the secondary flow path 24 for working medium gases extends parallel to and radially outward of the primary flow path 22.
- the fan section 14 includes a stator assembly 27 and a rotor assembly 28.
- the stator assembly has a fan containment case assembly 30 which forms the outer wall of the secondary flow path 24.
- the rotor assembly 28 includes a rotor disk 32 and a plurality of rotor blades 34. Each rotor blade 34 extends outwardly from the rotor disk 32 across the working medium flow paths 22 and 24 into proximity with the fan containment case assembly 30.
- Each rotor blade 34 has a root portion 36, an opposed tip 38, and a midspan portion 40 extending therebetween.
- a fan case liner 42 is disposed in the fan containment case assembly 30.
- the fan containment case assembly circumscribes the rotor assembly 28 in close proximity to the tips 38 of the rotor blades 34.
- the containment case assembly 30 includes a liner 42, a plurality of circumferentially adjacent rub strips 44 and a plurality of circumferentially adjacent acoustic panels 46 disposed radially inwardly of a support structure or a fan case 48.
- a plurality of fabric wraps 50 are disposed radially outwardly of the fan case.
- the fan case is typically a solid metal casing which forms a rigid structure to support the fabric wraps.
- the term "fabric" 50 includes, but is not limited to, tape, woven material or the like, and restrains a fan blade in the event of a fan blade loss.
- the rub strips 44 are formed from a relatively compliant material. The rub strips 44 permit the fan blades 34 to be in close proximity to the fan case to minimize the amount of air that flows around the fan blades, thus reducing fluid flow leakage around the fan blades to improve fan performance. In the event that the tip 38 of a fan blade 34 makes contact with the rub strips 44, the compliance of the rub strips minimizes the risk of damage to the fan blade 34.
- the fan case liner 42 is made from hardened material such as from alloys of stainless steel or nickel.
- the nickel alloy Inconel 718, or stainless steel alloys, such as AISI 321 or AISI 347, are examples of alloys that can be used to manufacture the liner.
- the liner is thus manufactured from material that is harder than the fan blade tip material which is typically titanium.
- the liner could be manufactured as arcuate segments which can then be bonded to the fan case. This arrangement, using a one-piece liner does not fall within the scope of the present invention, but its description has been retained to assist the reader in understanding the invention.
- a segmented fan case liner of an engine embodying the present invention is disposed radially outwardly of the rub strip 44 in the fan containment case assembly 30.
- Each segment 52 or shingle is offset from its adjacent shingle, yet there is an overlap region 54, shown clearly in FIG. 5, between adjacent shingles.
- the fan case liner 42 is attached to the fan case 48 by either rivets 56, or adhesives as shown in FIG. 4.
- the rivets 56 are located in the overlap region 54 between adjacent shingles.
- the detached blade In the event of a fan blade loss during engine operation, the detached blade is thrown radially outwardly. It typically will pass through the fan case 48 and will be caught by the fabric wraps 50 in the fan containment case assembly 30.
- the blade loss produces an imbalance in the rotor and causes the rotor to deflect radially outwardly in close proximity to the fan case.
- the separation between the fan blades and the inner surface of the fan case is minimized in modern engines to decrease the radial deflection of the rotor assembly. Due to the rotor deflection and the reduced clearance between the fan blades and the fan case, the fan blade tips rapidly cut away the compliant rub strip 44 in the innermost surface of the fan containment case assembly.
- the thin fan case liner made from shingles of hardened materials such as steel or nickel alloys, provides a skid surface for the relatively softer blades. The fan blades move circumferentially along on the skid-surface of the liner.
- the embedding of the blades in the fan case is eliminated or reduced; and as a result, the unwanted torque loading of the case is reduced. Without the hardened liner, the fan blades would continue to cut away and firmly embed in the fan case.
- the present invention thus provides for a system that allows for limiting rotor deflection during a fan blade loss event and provides a skid-plate function which eliminates or reduces the generation of additional torque loading on the case.
- the shingles provide a skid-surface for the fan blades to circumferentially rotate upon.
- the damage to the liner after a fan blade loss event is limited to the loss of one or more adjacent shingles.
- the remaining shingles continue to provide an effective skid-surface for the fan blades to glide on.
- a primary advantage of the present invention fan case liner is the minimization of damage to the fan case thus, resulting in a durable fan case in the event of a fan blade loss.
- the liner reduces the destructive cutting away of the fan case by the fan blades.
- a further advantage of the present invention fan case is its ability to provide an appropriate restraining structure to the deflection of the rotor shaft during a fan blade loss event.
- the liner reduces frictional forces, and as a result, reduces torque loads transmitted from the fan rotor to the case.
- Another advantage is the ease and cost of manufacturing and incorporating the hardened fan case liner of the present invention.
- the simplicity of the structure of the liner and the use of economical materials allows for cost effective manufacturing processes.
- current, prior art fan cases can be retrofitted to include the fan case liner in a cost effective manner. By incorporating the present invention liner, current engines limit damage to the fan containment case assembly and to the rotor shaft.
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)
Claims (4)
- Moteur de turbine à gaz (10) disposé autour d'un axe longitudinal (Ar), ledit moteur comprenant :un rotor (28) comprenant une soufflante, la soufflante étant dotée de pales (34) ; etun stator (27) comprenant un boítier (30) de soufflante disposé radialement vers l'extérieur par rapport à la soufflante, et comprenant en outre
un blindage (42) trempé segmenté ayant une surface interne, disposé dans le boítier de soufflante afin de circonscrire les pales de soufflante de sorte qu'à l'usage, dans le cas où il se produirait une perte de pale de soufflante, le blindage réduit l'endommagement du boítier de soufflante en permettant aux pales de soufflante de glisser le long de sa surface interne ; caractérisé en ce que ledit blindage (42) trempé segmenté comprend plusieurs bardeaux (52) disposés de manière circonférentielle dans le boítier (30) de soufflante, lesdits bardeaux étant par rapport aux bardeaux adjacents et formant une région de chevauchement (54) entre bardeaux adjacents. - Moteur de turbine à gaz selon la revendication 1, dans lequel le matériau de blindage est un alliage d'acier inoxydable ou de nickel.
- Moteur de turbine à gaz selon la revendication 1 ou 2, dans lequel lesdits bardeaux sont fixés sur le boítier (48) de soufflante par des rivets (56) situés dans la région de chevauchement (54) entre bardeaux adjacents.
- Moteur de turbine à gaz selon la revendication 1 ou 2, dans lequel lesdits bardeaux sont fixés sur le boítier (48) de soufflante avec de l'adhésif.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US96751997A | 1997-11-11 | 1997-11-11 | |
US967519 | 1997-11-11 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0922837A2 EP0922837A2 (fr) | 1999-06-16 |
EP0922837A3 EP0922837A3 (fr) | 2000-12-06 |
EP0922837B1 true EP0922837B1 (fr) | 2005-08-10 |
Family
ID=25512925
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19980309221 Expired - Lifetime EP0922837B1 (fr) | 1997-11-11 | 1998-11-11 | Boitier pour une soufflante |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP0922837B1 (fr) |
JP (1) | JPH11200813A (fr) |
DE (1) | DE69831124T2 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9644493B2 (en) | 2012-09-07 | 2017-05-09 | United Technologies Corporation | Fan case ballistic liner and method of manufacturing same |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2000220472A (ja) * | 1998-12-23 | 2000-08-08 | United Technol Corp <Utc> | ファンケ―スライナ― |
US7597040B2 (en) | 2003-07-30 | 2009-10-06 | The Boeing Company | Composite containment of high energy debris and pressure |
US7008173B2 (en) * | 2003-07-30 | 2006-03-07 | The Boeing Company | High energy containment device and turbine with same |
GB0501284D0 (en) * | 2005-01-21 | 2005-03-02 | Rolls Royce Plc | Aerofoil containment structure |
DE102009049841B4 (de) * | 2009-10-14 | 2015-01-15 | Mtu Friedrichshafen Gmbh | Gasturbomaschine und Brennkraftmaschine |
FR2964145B1 (fr) * | 2010-08-26 | 2018-06-15 | Safran Helicopter Engines | Procede d'accrochage de blindage sur carter de turbine et ensemble d'accrochage pour sa mise en oeuvre |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE3712829A1 (de) * | 1987-04-15 | 1988-11-03 | Mtu Muenchen Gmbh | Berstschutzring fuer turbotriebwerksgehaeuse |
US5447411A (en) * | 1993-06-10 | 1995-09-05 | Martin Marietta Corporation | Light weight fan blade containment system |
US5403148A (en) * | 1993-09-07 | 1995-04-04 | General Electric Company | Ballistic barrier for turbomachinery blade containment |
-
1998
- 1998-10-21 JP JP29928598A patent/JPH11200813A/ja active Pending
- 1998-11-11 DE DE69831124T patent/DE69831124T2/de not_active Expired - Lifetime
- 1998-11-11 EP EP19980309221 patent/EP0922837B1/fr not_active Expired - Lifetime
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9644493B2 (en) | 2012-09-07 | 2017-05-09 | United Technologies Corporation | Fan case ballistic liner and method of manufacturing same |
Also Published As
Publication number | Publication date |
---|---|
JPH11200813A (ja) | 1999-07-27 |
DE69831124T2 (de) | 2006-04-13 |
DE69831124D1 (de) | 2005-09-15 |
EP0922837A2 (fr) | 1999-06-16 |
EP0922837A3 (fr) | 2000-12-06 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US6637186B1 (en) | Fan case liner | |
US5607284A (en) | Baffled passage casing treatment for compressor blades | |
EP1096108B1 (fr) | Eléments statoriques de guidage de flux pour des turbines à gaz | |
US5823739A (en) | Containment case for a turbine engine | |
EP1245791B1 (fr) | Dispositif de rétention des aubes pour turbine à gaz | |
US6234747B1 (en) | Rub resistant compressor stage | |
US8662834B2 (en) | Method for reducing tip rub loading | |
US8657570B2 (en) | Rotor blade with reduced rub loading | |
US7972109B2 (en) | Methods and apparatus for fabricating a fan assembly for use with turbine engines | |
US6059523A (en) | Containment system for containing blade burst | |
US6394746B1 (en) | Gas turbine engine blade containment assembly | |
US20140064938A1 (en) | Rub tolerant fan case | |
EP1132576B1 (fr) | Virole de turbine comprenant un dispositif pour minimiser les gradients thermiques et procédé d'assemblage d'un moteur à turbine a gaz comportant une telle virole | |
EP2852741A1 (fr) | Dispositif permettant de repousser des débris | |
EP0922837B1 (fr) | Boitier pour une soufflante | |
EP3486433B1 (fr) | Joint à labyrinthe comportant des hauteurs de dent differente | |
CN111197596A (zh) | 具有磨料尖端的复合风扇叶片 | |
EP0927815A2 (fr) | Revêtement d'une virole d'une soufflante | |
EP0952309A2 (fr) | Joint d'étanchéité | |
EP1013894B1 (fr) | Moteur à turbine à gaz | |
EP3309364B1 (fr) | Système d'un moteur | |
GB2375798A (en) | A gas turbine engine fan blade containment assembly |
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): DE FR GB |
|
AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Kind code of ref document: A3 Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE |
|
AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
17P | Request for examination filed |
Effective date: 20010503 |
|
AKX | Designation fees paid |
Free format text: DE FR GB |
|
17Q | First examination report despatched |
Effective date: 20040401 |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
RTI1 | Title (correction) |
Free format text: FAN CASE LINER |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): DE FR GB |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D |
|
REF | Corresponds to: |
Ref document number: 69831124 Country of ref document: DE Date of ref document: 20050915 Kind code of ref document: P |
|
ET | Fr: translation filed | ||
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20060511 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20081106 Year of fee payment: 11 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: ST Effective date: 20100730 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20091130 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20121107 Year of fee payment: 15 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20121107 Year of fee payment: 15 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20131111 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20140603 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 69831124 Country of ref document: DE Effective date: 20140603 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20131111 |