Stator vane assembly for a gas turbine engine

A gas turbine engine has a stator vane assembly. The stator vane assembly includes an inner diameter shroud, an outer diameter shroud located radially outward from the inner diameter shroud, a vane extending radially outward from the first inner diameter shroud to the outer diameter shroud. The wedge clip is positioned horizontally through the vane to prevent the vane from being dislodged from the stator vane assembly.

FIELD

The present disclosure is directed to a gas turbine engine. More particularly, to a stator vane assembly and a method of installing a stator vane in a gas turbine engine.

BACKGROUND

Gas turbine engines include a compressor section, a turbine section, and a combustor section. Many gas turbine engines also include a fan that is driven by the turbine section. The fan generates a core airflow that is received by the compressor section and a bypass airflow that bypasses the compressor, turbine, and combustor sections and generates thrust. Stator vanes may be located upstream from the compressor and may condition the core airflow. It is undesirable for the stator vanes to become dislodged in response to ingestion of an object, such as a bird, in the core airflow.

SUMMARY

In various embodiments, a gas turbine engine having a stator vane assembly includes an inner diameter shroud, an outer diameter shroud located radially outward from the inner diameter shroud, and a vane extending radially outward from the first inner diameter shroud to the outer diameter shroud. A wedge clip is positioned horizontally through the vane to prevent the vane from being dislodged from the stator vane assembly. In various embodiments, the vane of gas turbine engine has a first end and a first slot located at the first end, the first slot being used to position the wedge clip.

The wedge clip of the gas turbine engine has a wedge portion that prevents the wedge portion from dislodging from the stator vane assembly. In various embodiments, the outer diameter shroud of the gas turbine engine is a single unit outer diameter shroud. The wedge clip of the gas turbine engine has a wedge portion with a first end having a first thickness and a bendable edge having a second thickness, wherein the first thickness is greater than the second thickness. The wedge portion of the wedge clip of the gas turbine engine springs to an initial position after being placed through a first slot at a first end of the vane. In various embodiments, a width of a wedge portion of the wedge clip and an angle of elevation of a first side of the wedge portion prevents the wedge clip and the vane from being dislodged. In various embodiments, a bendable edge of the wedge clip of the gas turbine engine allows the wedge clip to prevent the vane from dislodging from the outer diameter shroud.

In various embodiments of the gas turbine engine, a u-shape coupling of a wedge portion of the wedge clip to a non-wedge portion of the wedge clip allows the wedge portion to be a bendable wedge portion. In various embodiments of the gas turbine engine, a cornered and a quasi-corned design of the wedge clip self-centers the wedge clip to prevent a toggling of the wedge clip in a horizontal or a vertical direction.

In various embodiments, a method of assembling a stator vane assembly includes angling a vane into a first slot of an outer diameter shroud, aligning the vane into a first slot of an inner diameter shroud, and placing a wedge clip into a first slot of the vane to prevent the vane from dislodging from the stator vane assembly. In various embodiments, the method further includes bending a wedge portion of the wedge clip flush with the wedge clip when placing the wedge clip into the first slot of the vane. In various embodiments, the method further includes self-centering the wedge clip into the first slot of the vane when placing the wedge clip into the first slot of the vane. In various embodiments, the method further includes using a wedge portion of the wedge clip to act as a mechanical retention mechanism of the wedge clip to the stator vane assembly.

In various embodiments, a stator vane assembly includes an inner diameter shroud, an outer diameter shroud located radially outward from the inner diameter shroud, and a vane extending radially outward from the first inner diameter shroud to the outer diameter shroud, wherein a wedge clip is positioned horizontally through the vane to prevent the vane from being dislodged from the stator vane assembly. In various embodiments of the stator vane assembly, the vane has a first end and a first slot located at the first end, the first slot being used to position the wedge clip. In various embodiments of the stator vane assembly, the wedge clip has a wedge portion that prevents the wedge clip from dislodging from the stator vane assembly. In various embodiments of the stator vane assembly, the outer diameter shroud is a single unit outer diameter shroud.

In various embodiments of the stator vane assembly, a u-shape coupling of a wedge portion of the wedge clip to a non-wedge portion of the wedge clip allows the wedge portion to be a bendable wedge portion.

DETAILED DESCRIPTION

All ranges and ratio limits disclosed herein may be combined. It is to be understood that unless specifically stated otherwise, references to “a,” “an,” and/or “the” may include one or more than one and that reference to an item in the singular may also include the item in the plural.

As used herein, “aft” refers to the direction associated with the exhaust (e.g., the back end) of a gas turbine engine. As used herein, “forward” refers to the direction associated with the intake (e.g., the front end) of a gas turbine engine. An A-R-C axis is shown in various drawings to illustrate the axial, radial, and circumferential directions, respectively.

As used herein, “radially outward” refers to the direction generally away from the axis of rotation of a turbine engine. As used herein, “radially inward” refers to the direction generally towards the axis of rotation of a turbine engine.

In various embodiments and with reference toFIG. 1, a gas turbine engine20is provided. The gas turbine engine20may be a two-spool turbofan that generally incorporates a fan section22, a compressor section24, a combustor section26and a turbine section28. Alternative engines may include, for example, an augmentor section among other systems or features. In operation, the fan section22can drive coolant (e.g., air) along a bypass flow path B while the compressor section24can drive coolant along a core flow path C for compression and communication into the combustor section26then expansion through the turbine section28. Although depicted as a two-spool turbofan gas turbine engine20herein, it should be understood that the concepts described herein are not limited to use with two-spool turbofans as the teachings may be applied to other types of turbine engines including turbojet, turboprop, turboshaft, or power generation turbines, with or without geared fan, geared compressor or three-spool architectures.

The gas turbine engine20may generally comprise a low speed spool30and a high speed spool32mounted for rotation about an engine central longitudinal axis X-X′ relative to an engine static structure36or engine case via several bearing systems38,38-1, and38-2. It should be understood that various bearing systems38at various locations may alternatively or additionally be provided, including for example, the bearing system38, the bearing system38-1, and the bearing system38-2.

The low speed spool30may generally comprise an inner shaft40that interconnects a fan42, a low pressure compressor44and a low pressure turbine46. The inner shaft40may be connected to the fan42through a geared architecture48that can drive the fan42at a lower speed than the low speed spool30. The geared architecture48may comprise a gear assembly60enclosed within a gear housing62. The gear assembly60couples the inner shaft40to a rotating fan structure. The high speed spool32may comprise an outer shaft50that interconnects a high pressure compressor52and high pressure turbine54. A combustor26may be located between high pressure compressor52and high pressure turbine54. A mid-turbine frame57of the engine static structure36may be located generally between the high pressure turbine54and the low pressure turbine46. Mid-turbine frame57may support one or more bearing systems38in the turbine section28. The inner shaft40and the outer shaft50may be concentric and rotate via bearing systems38about the engine central longitudinal axis X-X′, which is collinear with their longitudinal axes. As used herein, a “high pressure” compressor or turbine experiences a higher pressure than a corresponding “low pressure” compressor or turbine.

In various embodiments, gas turbine20may include, for example, stator vane assembly200depicted inFIG. 2. Stator vane assembly200may include, for example, an outer diameter shroud240, an inner diameter shroud202, vanes204, bolts212, and wedge clips206. Outer diameter shroud240may include a plurality of outer diameter slots230. Inner diameter shroud202may include a plurality of inner diameter slots220. In various embodiments, inner diameter shroud202and outer diameter shroud210may be radially spaced apart such that vanes204may be arranged circumferentially about the X axis depicted inFIG. 1. Vanes204may be arranged to support stator vane assembly200and may be positioned to extend from inner diameter shroud202to outer diameter shroud240.

In various embodiments, vane204may have a first end214and a second end215. First end214may have a slot224associated with first end214. Second end215may have a slot226(shown inFIG. 5) associated with second end215. First end214of vane204extends through outer diameter shroud240via outer diameter slot230, thereby allowing wedge clip206to be inserted into slot224to hold vane204firmly into place. The insertion of wedge clip206into slot224may tend to prevent vane204from being dislodged from stator vane assembly200.

In various embodiments, outer diameter shroud240may be located radially outward from a plurality of vanes204and may retain the plurality of vanes204in place relative to stator vane assembly200. Outer diameter shroud240may be coupled to, for example, a front center body (FCB) with bolts212. In various embodiments, bolts212may be used to bolt outer diameter shroud to the FCB for bird strike resistance. In various embodiments, the addition of a single piece outer diameter shroud240allows for vanes204to remain secure, preventing vanes204from undesirably becoming dislodged in response to sufficient radially outward deflection of the outer diameter shroud240. In various embodiments, it may desirable to reduce radially outward deflection of outer diameter shroud240.

FIG. 3depicts a perspective view of a portion300of stator vane assembly200according to various embodiments. In various embodiments,FIG. 3shows a structural example of wedge clip206preventing vane204from being dislodged from stator assembly200. Vane204includes first end214, slot224, and a slot edge310. Wedge clip206includes a wedge portion304(e.g., a tine, locking arm, or locking tab) cut from the side of wedge clip206. In various embodiments, wedge clip206may be inserted horizontally into slot224to allow vane204to remain securely fastened to outer diameter shroud240. Wedge portion304extends radially such that wedge clip206is able to prevent wedge clip206from being dislodged. In various embodiments, wedge portion304may be bent radially to prevent wedge clip206from backing out slot224. Wedge portion304may, for example, bend and/or displace vertically during installation and spring back into place once wedge portion304extends through slot224. In various embodiments, wedge portion304may be designed such that the thickness of wedge portion304combined with the angle of elevation of wedge portion304prevents wedge clip206from being dislodged. In various embodiments, the wedge shape of wedge clip206may prevent the wedge portion304from pushing through slot224and hold wedge clip206in place to prevent circumferential migration due to vibration.

FIG. 4illustrates a top view perspective of wedge clip206of stator vane assembly200according to various embodiments. Wedge clip206includes a first side portion408, a first side portion418, a second side portion410, a third side portion428, a fourth side portion414, a fifth side portion404, a sixth side portion440, a seventh side portion430, a second side422, and a first side450. Wedge portion304of wedge clip206includes a first end444, a second end446, first side450, second side422, a third side421, and a bendable edge431.

In various embodiments, first side portion408is coupled to fourth side portion414at point A. Fourth side portion414is coupled to second side portion410point B. Second side portion410is coupled to third side portion428point C. Third side portion428is coupled to fifth side portion404at point D. Fifth side portion404is coupled to first side portion418at point E. First side portion418is coupled to first side450at point F. First side450is coupled to second side422at point G. Second side422is coupled to seventh side430at point H. Seventh side430is coupled to sixth side portion440at point I. Sixth side portion440is coupled to first side portion408at point J. In various embodiments, points A, B, E, F, G, I, and J are cornered points whose coupled sides corner to approximately 90 degrees. Points C and D are quasi-corned points whose coupled sides have angles equating to greater than 90 degrees. In various embodiments, point H has incoming sides that form a U-shape at point H. In various embodiments, wedge portion304is bendable or flexible at bendable edge431. In various embodiments, wedge portion304has a thickness at first end444of wedge portion304that increases in the direction of slot224toward vane204. In various embodiments, the thickness of is greater than the thickness at a second end446of wedge portion304.

FIG. 5illustrates a method500of installing vane204into stator vane assembly200according to various embodiments. In various embodiments, vane204is angled or rocked into outer diameter shroud240. Vane204is pushed or placed into inner diameter shroud202. Wedge clip206(depicted inFIG. 2) is placed into slot224. In various embodiments, wedge portion304(depicted inFIG. 3) of wedge clip206bends flush as wedge clip206is pushed through slot224. Wedge portion304may bend radially relative to the engine central longitudinal axis X-X′ so that wedge clip206clips in place to vane204, thereby minimizing the dislodging of vane204from stator vane assembly200. In various embodiments, wedge portion304may spring back into its initial position once wedge portion304passes through slot224. In various embodiments, wedge portion304acts as a mechanical retention mechanism. In various embodiments, the shape of wedge clip206centers wedge clip206(i.e., allows wedge clip206to self-center itself in slot224) with respect to vane204thereby preventing the toggling of wedge clip206radially, axially, and/or circumferentially relative to the engine central longitudinal axis X-X′.

In various embodiments, the outer diameter shroud240may be a single piece. As described, it is desirable for the outer diameter shroud240to resist movement in the radially outward direction which may occur, for example, during a bird strike (i.e., when a bird is ingested into gas turbine engine20).

While the disclosure is described with reference to exemplary embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted without departing from the spirit and scope of the disclosure. In addition, different modifications may be made to adapt the teachings of the disclosure to particular situations or materials, without departing from the essential scope thereof. The disclosure is thus not limited to the particular examples disclosed herein, but includes all embodiments falling within the scope of the appended claims.