Patent Application
20120251313
The described subject matter relates generally to gas turbine engines, and more particularly to vane retention provided therein.
Gas turbine engine vane assemblies, such as those provided downstream of the engine fan, may have slots defined through the outer engine case for receiving and retaining the outer ends of the vanes in place. A grommet may be inserted in the slots to surround and isolate the vane from the shroud. However, during a foreign object damage event, a damaged vane can cut the grommet and damage to other surrounding components. An adhesive such as a potting compound is sometimes used, either in conjunction with or in replacement of the grommet, but the use of such an adhesive generally complicates the installation and replacement of vanes. Existing vane retention systems also tend to be heavy and thus negatively affecting the engine's performance.
Accordingly, there is a need to provide improvement.
In one aspect, the described subject matter provides a vane assembly of a gas turbine engine comprising an annular casing having a series of circumferentially spaced openings defined therethrough; a plurality of circumferentially spaced vanes extending radially inwardly from the casing, an outer end of the respective vanes projecting radially outwardly from the casing through the respective openings, and an inner end of the vanes mounted to an inner portion of the casing; an elastomeric ring surrounding a circumferential outer surface of the casing, the elastomeric ring having a plurality of apertures in registry with the openings, each aperture receiving the projected outer end of a respective vane; and a strap of a non-metallic material extending around an outer periphery of the elastomeric ring and positioned to surround the projecting vane ends, the strap having metallic connectors configured to releaseably engage one another, the strap being under circumferential tension when the connectors are mutually engaged, the strap in tension compressing the elastomeric ring against the circumferential outer surface of the casing and biasing the vanes radially towards the inner portion of the casing.
In another aspect, the present invention provides a vane assembly for a gas turbine engine having an outer casing surrounding rotating blades of a rotor, the vane assembly comprising a tubular wall portion of the outer casing located downstream of the rotating blades, the wall portion having a series of circumferentially spaced openings defined therethrough; an inner shroud located inwardly and concentrically with the wall portion, the inner shroud and the wall portion in combination defining an annular flow path therebetween; a vane corresponding to each of the openings, radially extending between the wall portion and the inner shroud, an inner end of the vane being engaged with the inner shroud and an outer end of the vane being received in a corresponding one of the openings, the outer end of the vane projecting radially outwardly from an outer surface of the wall portion; an elastomeric ring surrounding the tubular wall portion, the elastomeric ring having a plurality of apertures each receiving the projected outer end of the respective vane; and a removable strap of a non-metallic material placed in a pre-tensioned condition around the elastomeric ring and against a circumferential outer surface of the tubular wall portion, the removable strap compressing the elastomeric ring and the outer ends of the respective vanes.
In a further aspect, the present invention provides a rotor assembly of a gas turbine engine comprising rotating blades; an annular outer casing having a series of circumferentially spaced apart openings defined therethrough; an inner shroud located inwardly concentric with the outer casing and downstream of the rotating blades, the inner shroud and the outer casing in combination defining an annular flow path therebetween; a vane corresponding to each of the openings, radially extending between the outer casing and the inner shroud, an inner end of the vane being engaged with the inner shroud and an outer end of the vane being received in a corresponding one of the openings, the outer end of the vane projecting radially outwardly from an outer surface of the outer casing; an elastomeric ring surrounding the outer ring, the elastomeric ring having a plurality of grommets each receiving the projected outer end of the respective vanes; and a strap of a non-metallic woven fabric having at least one pair of metallic connectors integrated with the strap, the strap forming a loop placed in a pre-tensioned condition around the elastomeric ring and against the outer surface of the outer casing when the paired connectors are releaseably engaged with each other, the pre-tensioned strap radially compressing the elastomeric ring and outer ends of the respective vanes.
Further details of these and other aspects of the described subject matter will be apparent from the detailed description and drawings included below.
Reference is now made to the accompanying drawings depicting aspects of the described subject matter, in which:
Referring to
Throughout this description, the axial, radial and circumferential directions are defined respectively with respect to the central axis, radius and circumference of the engine 10.
The vane tip 34 may include a generally rectangular slot 42 extending radially into the airfoil 36 between the leading and trailing edges 38, 40, in order to engage a corresponding web 44 of the inner shroud 26, as disclosed in U.S. Pat. No. 7,413,400, the full description of which is incorporated herein by reference. Alternatively, the vane tip 34 can have any other configuration suitable for engagement with the inner shroud 26.
The outer casing 24 has a series of circumferentially spaced openings 46 defined, for example through the wall portion downstream of the rotating blades 22 of the rotor assembly. Each of the openings 46 has a profile similar to but slightly larger than the vane root 32 such that the vane root 32 is loosely received in the opening 46 and radially and outwardly projects from the outer surface of the outer casing 24.
Referring now to
A removable strap 54 of a non-metallic material which in this embodiment, may be manufactured from a high strength woven fabric such as Kevlar®, is placed in a pre-tensioned condition around the elastomeric ring 48 to compress the elastomeric ring 48 against the circumferential outer surface of the outer casing 24 (see
The strap 54 of woven fabric may be manufactured as an endless loop and the connectors 56 may be integrated with the woven fabric during a weaving procedure. Alternatively, the strap 54 of woven fabric may be manufactured as a strap having opposite ends with the respective connectors 56 integrated with the opposite ends of the strap 54 during the weaving procedure. Therefore the strap 54 forms an endless loop only when the connectors 56 releasably engage each other.
Optionally, the elastomeric ring 48 may include a plurality of positioning elements 58a and 58b aligning in two circumferential lines, as shown in
Optionally, the elastomeric ring 48 including grommets 50 and the circumferential web portions 52 except for the positioning elements 58a and 58b, has a thickness substantially equal to the thickness of the grommets 50 such that the vane root 32 received within the respective grommet 50 is substantially flush with the outer surface of the elastomeric ring 48. Therefore, the pre-tensioned strap 54 not only provides a radial tension to the elastomeric ring 48, particularly to the grommets 50 against the circumferential outer surface of the tubular wall of the outer casing 24, but also provides radial retention of the vanes 30 during a normal engine operation and during a bird strike event. Furthermore, the structural flexibility of the strap 54 of woven fabric in combination with the grommets 50 of the elastomeric ring 48, provides dynamic damping of the vanes to reduce or eliminate vane vibration during engine operation.
Optionally, the pair of connectors 56 may include an apparatus for incrementally adjusting the pre-tensioned condition of the strap 54. For example, each of the paired connectors 56 may have mating hooks or apertures to be lined up to overlap each other, in order to receive a pin 60, as shown in
Alternatively, the strap 54 of woven fabric may be provided with a plurality of pairs of connectors 56. The pairs of connectors 56 are evenly spaced apart one pair from another in a circumferential direction of the strap 54, and are integrated with the strap 54 during a weaving procedure of the strap 54. The two connectors 56 in each pair are releasably engagable with each other and each pair of connectors is adapted to apply a circumferential tension force to the strap 54 by slightly shortening the circumference of the strap 54. The multiple pairs of connectors 56 allow the circumferential tension forces to be introduced to the strap 54 at more than one location around the circumference of the strap 54, thereby providing an evenly distributed pre-tensioned condition to the strap 54.
Alternatively, the strap 54 of woven fabric may be coated or impregnated with silicon or Teflon® (polytetrafluoroethylene) in order to prevent water absorption and to further facilitate strap movement over the elastomeric ring 48 for equalizing circumferential load distribution. The coating or impregnating procedure may be conducted on the material prior to or after the weaving procedure.
Also alternatively, the grommets 50 may have a thickness greater than the thickness of the circumferential web portions 52. Each of the grommets 50 radially extends into an annulus defined between the vane root 32 and the opening 46 as shown in
As a further alternative, the opening defined by each of the grommets 50 may be closed at the radial outer end thereof by a portion of the elastomeric ring 48, for example may be closed by an extension part of the adjacent web portion 52. The outer end of the vane 30 (vane root 32) is received within the aperture 49 (see
In comparison to the conventional metallic strap used for radially retaining outer ends of vanes in a vane assembly, the non-metallic strap 54 as above-described in combination with the elastomeric ring, provides a light-weight apparatus for a similar or higher stress retaining apparatus, which evenly distributes the load to the outer casing.
The above description is meant to be exemplary only, and one skilled in the art will recognize that changes may be made to the embodiments described without departure from the scope of the described subject matter. For example, a turbofan gas turbine engine is illustrated in the accompanying drawings as an exemplary application, however it should be understood that the described subject matter may also be applicable to engines of other types. The vane assembly in the above described embodiments need not be limited to the described configurations. The described subject matter may be combined with other configurations of vane assemblies of a gas turbine engines. Still other modifications which fall within the scope of the present invention will be apparent to those skilled in the art, in light of a review of this disclosure, and such modifications are intended to fall within the appended claims.
