FAN BLADE
A fan blade for the fan of a gas turbine engine has a radially outer tip portion which, in use, is adjacent to a fan case of the engine. The tip portion includes a movable sealing element for sealing a gap between the tip portion and the fan case. The sealing element movably adapts to changes in the spacing of the gap to maintain a seal between the tip portion and the fan case.
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This application is entitled to the benefit of British Patent Application No. GB 0807358.7, filed on Apr. 23, 2008.
FIELD OF THE INVENTIONThe present invention relates to a fan blade for the fan of a gas turbine engine.
BACKGROUND OF THE INVENTIONThe fan of a gas turbine engine comprises a cascade of circumferentially spaced an blades mounted at their radially inward ends on a disc and extending radially outwardly towards a fan case. To minimise aerodynamic losses and maintain the performance and stability of the fan blades, it is important to reduce leakage of air between the tips of the fan blades and the case. To this end, it is usual to have a close clearance between the tips and the case.
A conventional method of achieving a close clearance is to use fan track liners. These are positioned outboard of the fan blades on the fan case, and typically comprise an abradable liner supported by an aluminium honeycomb structure. The abradable liner consists of Nomex™ (available from DuPont) honeycomb filled with lightweight epoxy filler. The liner forms an aerodynamic seal between the fan blades and the case.
In general, abradable liners seal the tip well at maximum engine speed, but less so at cruise when centrifugal forces on the blade are lower, and clearance between the tip and the fan case increases. This causes an efficiency drop at cruise. Under certain operating conditions (e.g. manoeuvre loading or abnormal engine conditions such as red line/over speed) it is acceptable for fan blades to make rubbing contact with the abradable liner. However, for every rub event, the efficiency drop at cruise increases.
Further, such contacts carry the risk of damaging the blade, and reducing its longevity. This risk can be higher with a blade formed of composite material, which may be susceptible to delamination or matrix damage under frictional loading. Ultimately, damage from excessive rubbing contacts accumulating over time may cause premature blade failure, particularly in blades formed of composite material.
SUMMARY OF THE INVENTIONThus, in a first aspect, the present invention provides a fan blade for the fan of a gas turbine engine, the blade having a radially outer tip portion which, in use, is adjacent to a fan case of the engine, the tip portion including a movable sealing element for sealing a gap between the tip portion and the fan case, wherein the sealing element movably adapts to changes in the spacing of the gap to maintain a seal between the tip portion and the fan case.
In this way, sealing functionality is transferred from the fan case to the fan blade, and the use of an abradable liner on the fan case can be avoided. This reduces engine weight, as well as helping to avoid rubbing contact damage to the fan blade.
The fan blade can have one sealing element, typically running the length of the radially outer edge of the blade. Alternatively, the blade can have a plurality of sealing elements, for example in an overlapping arrangement, and again typically running along the radially outer edge of the blade.
The sealing element can be formed integrally with the blade. However, preferably, the sealing element is removably attached to the blade. For example, the blade can have a keyway slot or slots for slidingly receiving the sealing element(s). A removably attached sealing element can, advantageously, be easily replaced if it becomes damaged.
The sealing element may be formed of flexible material, which flexes to adapt to changes in the spacing of the gap. For example, the element can be formed as a strip e.g. of flexible plastic or rubber. Or the element can be formed as brush, with the fibres of the brush, in use, extending across the gap. The fibres of a brush sealing element may be formed of carbon fibre.
Preferably, the sealing element responds to centrifugal loading by extending across the gap. For example, the element may have a curved or bent cross-section that straightens out under centrifugal loading to extend across the gap.
The fan blade may be configured to promote air film lubrication of the interface between the sealing element and the fan case. This can reduce the wear on the sealing element and, to a lesser extent, on the fan case.
A further aspect of the present invention provides a gas turbine engine having a fan comprising circumferentially spaced fan blades according to the previous aspect.
The fan case may have an acoustic liner at the interface between the sealing element and the fan case. This can reduce engine noise, and is possible because an abradable liner at this position is not needed.
The fan case may have debris removal channels at the interface between the sealing element and the fan case.
The keyway 2 can be formed in the body of a composite or a metallic blade, or can be formed by a separate part, e.g. facing side plates, attached to the tip of such a blade.
The sealing element can be configured so that, under the pressure differential produced during operation, an air film is generated which lubricates the space between the sealing element and the case. In this way, excessive wear of the element can be avoided.
Instead of being attached via keyway 2, the sealing element can be adhesively bonded, or mechanically fastened in other ways to the tip of the blade. Preferably, the element is attached in such a way as to allow extraction and replacement during overhaul. However, particularly with a composite blade, the sealing element can be integrated with the blade, for example by moulding or co-moulding.
Other configurations of the flexible sealing element are possible. For example, instead of an element formed as a strip running along the radially outer edge of the blade, a brush sealing element could be adopted, in which a plurality of fibres extend from the blade tip towards the casing. These can be bonded in place or mechanically attached via side plates. For example, the fibres can be embedded at their radially inner ends in a retaining head, which itself can be held in a keyway at the radially outer edge of the blade. When the blade is formed from fibre-reinforced composite material, the fibres of the composite can themselves extend out of the matrix of composite at the blade tip to form the brush sealing element.
A brush sealing element may be constructed from pure carbon fibres. Break up of the carbon then produces lubrication on the fan case.
The strip sealing element of
Other shapes are possible, however. For example, the flexible sealing element may have one or more kinks serving as hinges about which the portion of the flexible sealing element radially outward of the kink rotates under centrifugal loading to straighten the element.
Further embodiments of the sealing element do not rely on the intrinsic flexibility of a strip or brush, to achieve some or all of the movability to adapt to changes in the spacing between the fan blade and the casing.
For example,
The sealing element of any of the above embodiments may have a portion formed of relatively low friction material at its radially outer edge. For example, the low friction material portion can be of carbon, PTFE or PEEK. It may be applied as a coating to the sealing element. The material may be reapplied at intervals to regain efficiency losses.
As well as the improvement in engine performance that can be achieved with the sealing element, for composite blades there is also a reduced risk of blade delamination due to tip rubs. Further, the sealing element can accommodate casing distortions. Additionally, eliminating the abradable liner from the fan case can reduce engine weight (providing further performance improvements) and allows an acoustic fan track liner to be provided with the potential to significantly reduce engine noise.
Because the sealing element has a relatively large clearance to the casing when the engine is stationary, the procedure for mounting fan blades onto the engine is facilitated. Further, once mounted, the ability of the sealing element to tolerate variation in blade length can reduce the amount of blade adjustment/shimming that has to be performed. Also, abradable liners need to be machined on engine when installed to provide the required fit, but with the sealing element this requirement is removed.
While the invention has been described in conjunction with the exemplary embodiments described above, many equivalent modifications and variations will be apparent to those skilled in the art when given this disclosure. Accordingly, the exemplary embodiments of the invention set forth above are considered to be illustrative and not limiting. Various changes to the described embodiments may be made without departing from the spirit and scope of the invention.
Claims
1. A fan blade for the fan of a gas turbine engine, the blade having a radially outer tip portion which, in use, is adjacent to a fan case of the engine, the tip portion including a movable sealing element for sealing a gap between the tip portion and the fan case, wherein the sealing element movably adapts to changes in the spacing of the gap to maintain a seal between the tip portion and the fan case.
2. A fan blade according to claim 1, wherein the sealing element is formed integrally with the blade.
3. A fan blade according to claim 1, wherein the sealing element is removably attached to the blade.
4. A fan blade according to claim 1, wherein the sealing element is formed of flexible material which flexes to adapt to changes in the spacing of the gap.
5. A fan blade according to claim 1, wherein the sealing element responds to centrifugal loading by extending across the gap.
6. A fan blade according to claim 1, which is configured to promote air film lubrication of the interface between the sealing element and the fan case.
7. A gas turbine engine having a fan comprising circumferentially spaced fan blades according to claim 1.
8. A gas turbine according to claim 7, wherein the fan case has an acoustic liner at the interface between the sealing element and the fan case.
9. A gas turbine according to claim 7, wherein the fan case has debris removal channels at the interface between the sealing element and the fan case.
Type: Application
Filed: Mar 31, 2009
Publication Date: Oct 29, 2009
Applicant: Rolls-Royce PLC (London)
Inventor: Kristofer John Bottome (Nottingham)
Application Number: 12/415,031
International Classification: F01D 11/08 (20060101); F01D 25/00 (20060101);