The application relates generally to an apparatus for actuating a variable guide vane in a compressor or a turbine.
Gas turbine engines sometimes have variable guide vanes (VGVs) disposed in an inlet section of an airflow duct of a compressor or turbine section. The guide vanes are adjustable in an angular orientation in order to control the airflow being directed through the airflow duct. An actuator positioned outside the airflow duct is conventionally used to actuate adjustment of the angular orientation of the VGVs. Various torque transfer arrangements have been created for connection between the actuator and the VGVs.
For VGV actuating systems with radial VGV (vanes oriented generally radially relative to the engine centerline), the VGV system is typically designed with a rotary actuator and vane actuating links. The contact between the rotary actuator and the actuating links has to be reduced in order to cater for greater VGV angle range. This results in increased wear at the link-actuator interface which leads to system inaccuracy.
In accordance with a general aspect, there is provided a variable guide vane apparatus for a compressor or a turbine, comprising: a unison ring rotatable about a central axis thereof, the unison ring having an array of circumferentially spaced-apart drive pins; a set of variable guide vanes (VGV) circumferentially distributed around the central axis and mounted for rotation about respective spanwise axes of the vanes, the spanwise axes extending non-parallel to the central axis of the unison ring; and a plurality of actuating arms operatively connected to respective variable guide vanes for rotation therewith, the actuating arms each including a fork having a pair of spaced apart fingers with inwardly facing surfaces defining a slot therebetween, a corresponding one of said drive pins slidably received in the slot; wherein in a plane normal to a longitudinal axis of the slot, the inwardly facing surfaces have opposed end portions flaring outwardly from an intermediate throat in a direction away from the slot.
In accordance with another general aspect, there is provided a gas turbine engine comprising: a casing circumferentially extending around a central axis, vanes circumferentially distributed around the central axis, the vanes rotatably mounted to the casing for rotation about respective spanwise axes of the vanes, the spanwise axes of the vanes being transversal to the central axis, a unison ring mounted for rotation about the central axis; drive pins mounted to the unison ring; actuating arms operatively connected to respective vanes for rotation therewith, each actuating arm including a fork having a pair of fingers with inwardly facing surfaces defining a slot, an associated pin of the drive pins slidably engaged in the slot, the inwardly facing surfaces of the slot being profiled with top and bottom outwardly flaring sections to accommodate angular misalignment between the associated pin and the fork throughout a range of motion of the associated pin along the slot.
Reference is now made to the accompanying figures in which:
It should be noted that the terms “axial”, “radial” and “circumferential” are used with respect to the centerline or central axis 11 of the engine 10.
In this example, the compressor section 14 defines an annular airflow duct 25 having an axial inlet section (not numbered) to direct an airflow axially inwardly into the annular airflow duct 25 of the compressor section 14, as indicated by the flow arrows. A variable guide vane (VGV) apparatus 26 is mounted to the compressor section 14 and has a plurality of variable inlet guide vanes 28 (VIGVs) positioned and rotatably supported within the inlet section of the airflow duct 25. The VIGVs 28 are rotatable about respective spanwise axes 30 thereof, which are angled to the central axis 11 of the engine (i.e. non-parallel to the engine axis 11). The angular orientation of the VIGVs 28 about the respective spanwise axes 30 is adjustable such that the airflow entering the inlet section of the airflow duct 25 is controlled by the VIGVs 28. The VIGVs are configured to orient the flow before entering the first stage of compressor blades of the compressor section 14. The VGV apparatus is configured to vary an angle of attack of its vanes depending of the operating conditions of the gas turbine engine. However, it is understood that VGVs may be used at other locations within the engine 10.
Referring concurrently to
According to one embodiment, the actuating link or arm 35 has a base 38 and a fork 36 having a pair of spaced-apart fingers extending in a parallel relationship from the base 38. The base 38 defines a central opening for receiving a stem 48 projecting from a radially outer end of each VIGV 28. The stem 48 may be connected to or integrated with each of the VIGVs 28, and extending coaxially with respect the axis 30 of the associated VIGV 28. For example, as shown in
As best shown in
Also, as the pivot axes 30 of the vanes 28 are not parallel to engine axis 11 and, thus, to the rotation axis of the unison ring 32, but rather oriented at an angle with respect thereto. As a result and as shown in
As shown in
Alternatively, the fork profiled surface could be designed as a single radius from top to bottom of the fork arm or even chamfered top and bottom of the fork with the pin contact interface as a line contact. Nonetheless, combining a flatten area with outwardly flaring top and bottom areas allows to increase contact area to minimize wear rate while providing the required freedom of angular movement between the pin the forks. With such a pin-fork arrangement, the interface can then be optimized to increase the contact surface between the pin and fork.
According to these embodiments, the width of the slot varies along the height (h) of the slot. This can be appreciated from
Therefore, according to at least some embodiments, the accuracy and durability at the pin-fork interface may be improved by: 1) introducing variable profile to the fork surface to allow for drive pin angle change over full range of motion of the vanes.
Furthermore, as shown in
As shown in
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 departing from the scope of the invention disclosed. For example, it is understood that the various features of the VGV actuating system are not limited to turbofan applications. Indeed, they could be applied to any engines, including turboshaft, turboprop, APU engines as well as non-gas turbine engines. Also, it is understood that the VGVs are not limited to VIGVs as exemplified herein above. Any variable guide vane apparatus having VGVs with pivotal axes angled to the engine centerline could benefit from the various aspects of the present invention. For instance, VGVs apparatus in the turbine section of the engine could integrate at least some of the various features described herein above. 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.
The present application claims priority on U.S. Provisional Patent Application No. 62/723,684, filed on Aug. 28, 2018 and U.S. Provisional Patent Application No. 62/723,708, filed on Aug. 28, 2018, the entire content of which is herein incorporated by reference.
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