Patent Grant
12000293
The present disclosure relates generally to gas turbine engines, and more specifically to variable vane assemblies of gas turbine engines.
Gas turbine engines are used to power aircraft, watercraft, power generators, and the like. Gas turbine engines typically include an engine core having a compressor, a combustor, and a turbine. The compressor compresses air drawn into the engine and delivers high pressure air to the combustor. In the combustor, fuel is mixed with the high pressure air and is ignited. Products of the combustion reaction in the combustor are directed into the turbine where work is extracted to drive the compressor and, sometimes, an output shaft. Left-over products of the combustion are exhausted out of the turbine and may provide thrust in some applications.
Gas turbine engines also typically include vane assemblies arranged within the engine components, such as inlet guide vanes and stator vanes. To provide for the necessary stall or surge margin at different power settings throughout operation of the gas turbine engine, variable, or adjustable, vanes may be utilized, such as variable inlet guide vanes and/or variable stator vanes. It is important to position of the vanes with extreme precision in order to accurately direct airflow within the engine.
The present disclosure may comprise one or more of the following features and combinations thereof.
According to a first aspect of the present disclosure, a vane adjustment assembly for a gas turbine engine includes a plurality of vanes extending radially outward relative to a central axis of the gas turbine engine, an annular ring arranged radially outward of the central axis and coupled to the plurality of variable vanes, and a ring adjustment assembly. The ring adjustment assembly includes (i) a base frame mounted on the annular ring and including a support body extending axially away from the annular ring, the support body having a first cylindrical cavity formed therethrough that extends radially and that is offset axially from the annular ring, (ii) a first collar that is cylindrical and removably arranged within the first cylindrical cavity, the first collar having a second cylindrical cavity formed therein and opening radially outwardly, (iii) a second collar that is cylindrical and removably arranged within the second cylindrical cavity of the first collar, and (iv) a roller pin fixedly coupled to a radially outer surface of the second collar.
In some embodiments, a first central axis of the second cylindrical cavity is offset from a second central axis of the first collar and a third central axis of the roller pin is offset from a fourth central axis of the second collar, and the first collar is configured to be selectively arranged at a plurality of rotational positions within the first cylindrical cavity and the second collar is configured to be selectively arranged at a plurality of rotational positions within the second cylindrical cavity of the first collar such that the roller pin is configured to be positioned at a plurality of distinct roller pin positions each corresponding to a rotational position of the first collar and a rotational position of the second collar.
In some embodiments, the first collar is fixed relative to the first cylindrical cavity when arranged within the first cylindrical cavity, and the second collar is fixed relative to the second cylindrical cavity of the first collar when the second collar is arranged within the second cylindrical cavity. In some embodiments, the first cylindrical cavity is generally cylindrical, an inner circumferential surface defining the first cylindrical cavity substantially corresponds to an outer circumferential surface of the first collar such that the first collar may be arranged at the plurality of rotational positions within the first cylindrical cavity, and an inner circumferential surface defining the second cylindrical cavity substantially corresponds to an outer circumferential surface of the second collar such that the second collar may be arranged at the plurality of rotational positions within the second cylindrical cavity.
In some embodiments, the first collar is arranged within the first cylindrical cavity with an interference fit such that the first collar is securely held within the first cylindrical cavity. In some embodiments, the second collar is arranged within the second cylindrical cavity with an interference fit such that the second collar is securely held within the second cylindrical cavity.
In some embodiments, the inner circumferential surface defining the second cylindrical cavity is tapered in a radial direction of the annular ring such that a diameter of the second cylindrical cavity at a radially outermost side of the second cylindrical cavity is larger than a diameter of the second cylindrical cavity at a radially innermost side of the second cylindrical cavity, and the outer circumferential surface of the second collar is tapered such that a diameter of the second collar at a radially outermost side of the second collar is larger than a diameter of the second collar at a radially innermost side of the second collar.
In some embodiments, the tapered inner circumferential surface of the second cylindrical cavity and the tapered outer circumferential surface of the second collar cause a retention force of the second cylindrical cavity on the second collar to increase the further radially inwardly the second collar is arranged within the second cylindrical cavity.
In some embodiments, the inner circumferential surface defining the second cylindrical cavity includes at least one first step such that the inner circumferential surface includes a first stepped portion and a second stepped portion having a smaller diameter than the first stepped portion, and the outer circumferential surface of the second collar includes at least one second step such that the outer circumferential surface includes a third stepped portion corresponding to the first stepped portion and a fourth stepped portion corresponding to the second stepped portion and having a smaller diameter than the third stepped portion.
In some embodiments, the inner circumferential surface defining the first cylindrical cavity includes at least one third step such that the inner circumferential surface includes a fifth stepped portion and a sixth stepped portion having a smaller diameter than the fifth stepped portion, and the outer circumferential surface of the first collar includes at least one fourth step such that the outer circumferential surface includes a seventh stepped portion corresponding to the fifth stepped portion and an eighth stepped portion corresponding to the sixth stepped portion and having a smaller diameter than the seventh stepped portion.
In some embodiments, the support body of the base frame extends away from a first axially facing surface of the annular ring. In some embodiments, the base frame includes a bracket that is fixedly mounted on the annular ring, and the support body of the base frame extends away from a first axially facing surface of the bracket.
In some embodiments, the roller pin is selectively movably coupled to a casing of the gas turbine engine such that movement of the roller pin relative to the casing further adjusts the position of the annular ring relative to the casing, the roller pin is selectively movably coupled to the casing via a cam plate that is slidably coupled to the casing and slidable relative thereto, and the cam plate includes at least one slot within which the roller pin is slidably arranged.
In some embodiments, sliding of the cam plate relative to the casing in an axial direction causes the roller pin to slidably move within the at least one slot and further adjust a position of the annular ring relative to the casing, and the roller pin includes a roller pin head configured to be slidably arranged within the at least one slot and engage with edges of the at least one slot.
A vane adjustment assembly for a gas turbine engine includes an annular ring arranged radially outward of a central axis of the gas turbine engine and coupled to a plurality of variable vanes and a ring adjustment assembly. The ring adjustment assembly includes (i) a base frame mounted on the annular ring having a first cavity formed therethrough that is offset axially from the annular ring (ii) a first collar removably arranged within a first cavity formed in the annular ring, the first collar having a second cavity eccentrically formed therein, (iii) a second collar removably arranged within the second cavity of the first collar, and (iv) a roller pin eccentrically arranged on the second collar.
In some embodiments, the first collar is configured to be selectively arranged at a plurality of rotational positions within the first cavity and the second collar is configured to be selectively arranged at a plurality of rotational positions within the second cavity of the first collar such that the roller pin is configured to be positioned at a plurality of distinct roller pin positions each corresponding to a rotational position of the first collar and a rotational position of the second collar.
In some embodiments, the first cavity is generally cylindrical, an inner circumferential surface defining the first cavity substantially corresponds to an outer circumferential surface of the first collar such that the first collar may be arranged at the plurality of rotational positions within the first cavity, and an inner circumferential surface defining the second cavity substantially corresponds to an outer circumferential surface of the second collar such that the second collar may be arranged at the plurality of rotational positions within the second cavity.
In some embodiments, the first collar is arranged within the first cavity with an interference fit such that the first collar is securely held within the first cavity, and the second collar is arranged within the second cavity with an interference fit such that the second collar is securely held within the second cavity.
In some embodiments, the inner circumferential surface defining the second cylindrical cavity is tapered in a radial direction of the annular ring such that a diameter of the second cylindrical cavity at a radially outermost side of the second cylindrical cavity is larger than a diameter of the second cylindrical cavity at a radially innermost side of the second cylindrical cavity, and the outer circumferential surface of the second collar is tapered such that a diameter of the second collar at a radially outermost side of the second collar is larger than a diameter of the second collar at a radially innermost side of the second collar.
In some embodiments, the roller pin is selectively movably coupled to a casing of the gas turbine engine such that the plurality of distinct roller pin positions each corresponding to a rotational position of the first collar and a rotational position of the second collar each further correspond to distinct positions of the roller pin relative to the casing and distinct positions of the annular ring relative to the casing, the roller pin is selectively movably coupled to the casing via a cam plate that is slidably coupled to the casing and slidable relative thereto, and the cam plate includes at least one slot within which the roller pin is slidably arranged.
According to a further aspect of the present disclosure, a method of adjusting a vane assembly of a gas turbine engine includes providing a plurality of vanes of the vane assembly, the plurality of vanes extending radially outward relative to a central axis of the gas turbine engine, arranging an annular ring radially outward of the central axis, and coupling the annular ring to the plurality of vanes. The method can further include mounting a base frame on the annular ring, the base frame including a support body extending axially away from the annular ring, the support body having a first cylindrical cavity formed therethrough that extends radially and that is offset axially from the annular ring, selectively and removably arranging a first collar that is cylindrical within the first cylindrical cavity at a first rotational position therein, the first collar having a first cylindrical cavity formed therein and opening radially outwardly, fixedly coupling a roller pin to a radially outer surface of a second collar that is cylindrical, and selectively and removably arranging the second collar within the second cylindrical cavity of the first collar at a second rotational position therein so as to locate the roller pin at a first discrete roller pin position.
In some embodiments, a first central axis of the first cylindrical cavity is offset from a second central axis of the first collar and a third central axis of the roller pin is offset from a fourth central axis of the second collar, and the first collar is configured to be selectively arranged at a plurality of rotational positions including the first rotational position within the first cylindrical cavity and the second collar is configured to be selectively arranged at a plurality of rotational positions including the second rotational position within the second cylindrical cavity of the first collar such that the roller pin is configured to be positioned at a plurality of distinct roller pin positions including the first discrete roller pin position each corresponding to a rotational position of the first collar and a rotational position of the second collar.
These and other features of the present disclosure will become more apparent from the following description of the illustrative embodiments.
For the purposes of promoting an understanding of the principles of the disclosure, reference will now be made to a number of illustrative embodiments illustrated in the drawings and specific language will be used to describe the same.
The present disclosure is related to vane adjustment assemblies 36, 136, 236, 336, 436 configured to be utilized in a gas turbine engine 10, in particular vane adjustment assemblies 36, 136, 236, 336, 436 including a ring adjustment assembly 40, 140, 240, 340, 440 having a base plate or frame 42, 142, 242, 342, 442, a first collar 52, 152, 252, 352, 452, a second collar 62, 162, 262, 362, 462 arranged in an eccentrically formed first cavity 54, 154, 254, 354, 454, and a roller pin 70, 170, 270, 370, 470 eccentrically coupled to the second collar 62, 162, 262, 362, 462. The eccentricity of the first cavity 54, 154, 254, 354, 454 and the arrangement of the roller pin 70, 170, 270, 370, 470 on the second collar 62, 162, 262, 362, 462 enable the first and second collars 52, 152, 162, 252, 262, 352, 362, 452, 462 to be selectively arranged at a plurality of rotational positions within the first cavity 54, 154, 254, 354, 454 and relative to the second collar 62, 162, 262, 362, 462, respectively, such that the roller pin 70, 170, 270, 370, 470 can be positioned at distinct roller pin positions each corresponding to a rotational position of the first collar 52, 152, 252, 352, 452 and a rotational position of the second collar 62, 162, 262, 362, 462. A person skilled in the art will understand that the disclosed vane adjustment assemblies 36, 136, 236, 336, 436 may be utilized in any type of engine similar to a gas turbine engine or any turbomachinery including vanes.
A vane adjustment assembly 36 according to a first aspect of the present disclosure is shown in
The engine 10 includes a casing 24, which may be formed as a single component or multiple cojoined components, that surrounds the various sections of the engine 10, including the compressor 13, the combustor 16, and the turbine 17. Illustratively, the compressor 13 and/or turbine 17 sections may include multiple stages of a plurality of vanes 26 arranged between stages of bladed rotors, as shown in
In some embodiments, the plurality of vanes 26 include individual vane airfoils 26A having inner and outer platforms 261, 260, as shown in
In the illustrative embodiment, the vane adjustment assembly 36 is configured to be utilized in the compressor or turbine sections 13, 17 of the engine 10, although in other embodiments, a person skilled in the art could envision the adjustment assembly 36, or any other vane assemblies described herein, being utilized in other sections of the engine 10, such as with variable fan outlet guide vanes 22 arranged downstream of the fan 12 or inlet guide vanes arranged upstream of the fan 12.
As shown in
Illustratively, the annular ring 30 is formed as a fully annular ring that is movably or slidably arranged relative to the casing 24 so as to rotate annularly relative thereto, as shown in
As shown in
The cam plate 91 includes a plurality of slots 93, 94, 95, 96 which, when the cam plate 91 is arranged on the support plate 92, are aligned with the individual vane stages, for example, shown in
With the cam plate 91, the roller pin 70 of the vane adjustment assembly 36 may be moved to a plurality of distinct roller pin positions that, in addition to each corresponding to a rotational position of the first collar 52 and a rotational position of the second collar 62 (i.e. due to the rotational position of the first collar 52 within the recess 46 and the rotational position of the second collar 62 within the first collar 52), each further correspond to distinct positions of the roller pin 70 relative to the casing 24. Moreover, due to the roller pin 70 being coupled to the annular ring 30 via the adjustable collars 52, 62, the movement of the roller pin 70 relative to the casing 24 via the cam plate 91 will also affect the positioning of the annular ring 30 relative to the casing 24.
In order to further fine-tune and adjust the positioning of the plurality of vanes 26 via the positioning of the annular ring 30, the vane adjustment assembly 36 further includes the ring adjustment assembly 40 shown in
As can be seen
As shown in greater detail in
As can be seen in
The ring adjustment assembly 40 further includes the first collar 52 and the second collar 62, as shown in
By way of a non-limiting example, the recess 46 and the first collar 52 may include cross-sectional shapes that are polygonal, including any number of sides that would enable placement of the first collar 52 fixedly therein. For example, the first collar 52 and the recess 46 may each include a cross-sectional shape that is a polygon and includes an equal number of sides. In some embodiments, the cross-sectional shape of the first collar 52 may include 10 sides, and the cross-sectional shape of the recess 46 may include 10 sides. In another example, the cross-sectional shape of one of the recess 46 and the first collar 52 may include more sides than the cross-sectional shape of the other of the recess 46 and the first collar 52, and the corners formed by the multiple sides of the first collar 52 nevertheless rest within the recess 46 while still fixing the first collar 52 at various rotational positions within the recess 46. In some embodiments, the first collar 52 and the recess 46 each include a polygonal shape having 3 to 30 sides.
In the illustrative embodiment, the first collar 52 is formed cylindrically and includes an upper lip 55L formed on the outer circumferential surface 55 of the first collar 52, as shown in
The first collar 52 further includes a first cavity 54 formed therein, also referred to as a first cylindrical cavity 54, as shown in
As can be seen in
The first collar 52 further includes a second plurality of spline grooves 59 formed on the inner circumferential surface 53. The second plurality of spline grooves 59 are formed similarly to the spline teeth 68 formed on the outer circumferential surface 65 of the second collar 62 so as to engage the spline teeth 62 and fixedly secure the second collar 62 within the first cavity 54 such that it cannot rotate relative thereto. As described herein, spline teeth may refer to any type of geared tooth, such as flat sided teeth for example, capable of interacting with corresponding grooves. The size of teeth may be related to manufacturing, tooth stress, assembly, robustness, etc.
As can be seen in
Illustratively, the first collar 52 includes 30 spline teeth 58 formed on the outer circumferential surface 55, as shown in
As can be seen in
By way of a non-limiting example, the first cavity 54 and the second collar 62 may include cross-sectional shapes that are polygonal, including any number of sides that would enable placement of the second collar 62 fixedly therein. For example, the second collar 62 and the first cavity 54 may each include a cross-sectional shape that is a polygon and includes an equal number of sides. In some embodiments, the cross-sectional shape of the second collar 62 may include 10 sides, and the cross-sectional shape of the first cavity 54 may include 10 sides. In another example, the cross-sectional shape of one of the first cavity 54 and the second collar 62 may include more sides than the cross-sectional shape of the other of the first cavity 54 and the second collar 62, and the corners formed by the multiple sides of the second collar 62 nevertheless rest within the first cavity 54 while still fixing the second collar 62 at various rotational positions within the first cavity 54. In some embodiments, the second collar 62 and the first cavity 54 each include a polygonal shape having 3 to 30 sides.
In the illustrative embodiment, the second collar 62 is formed cylindrically and includes an outer circumferential surface 65, as shown in
The roller pin 70 is arranged on a top surface 62T of the second collar 62, as shown in
As can be seen in
The roller pin 70 can include a central cylindrical shaft 72 that extends radially away from the second collar 62, as shown in
As can be seen in
Illustratively, the second collar 62 includes 32 spline teeth 68 formed on the outer circumferential surface 65, as shown in
In operation, the first collar 52 is configured to be selectively arranged at a plurality of rotational positions within the recess 46 and the second collar 62 is configured to be selectively arranged at a plurality of rotational positions within the first cylindrical cavity 54 of the first collar 52. In particular, the second collar 62, along with the attached roller pin 70, is configured to be removed from and reinserted into the first cavity 54 of the first collar 52, and similarly, the first collar 52 is configured to be removed from and reinserted into the recess 46 of the base plate 42. In this way, the first collar 52 can be arranged at a plurality of rotational positions within the recess 46, in particular, for example, at one of the 30 spline teeth 58 positions. Similarly, the second collar 62 can be arranged at a plurality of rotational positions within the first cavity 54, in particular, for example, at one of the 32 spline teeth 68 positions.
Due to the eccentricity of the first cavity 54 relative to the recess 46 (or in other words, the eccentricity of the first cavity 54 relative to the outer surface 53 of the first collar 52) and the eccentricity of the roller pin 70 arrangement on the second collar 62, the roller pin 70 can be positioned at a plurality of distinct roller pin positions each corresponding to a rotational position of the first collar 52 and a rotational position of the second collar 62. In addition to the movement of the roller pin 70 within the cam plate 91 having an effect on the position of the annular ring 30, the roller pin 70 position may be even further fine-tuned by selectively arranging the first and second collars 52, 62 within the recess 46 and first cavity 54 to achieve a precise desired roller pin position 70.
For example, for an offset of approximately 0.05 inches, the roller pin 70 may be positioned at any one of the discrete roller positions shown in
According to the present disclosure, a method of adjusting a vane assembly of a gas turbine engine can include providing a plurality of vanes of the vane assembly, the plurality of vanes extending radially outward relative to a central axis of the gas turbine engine, arranging an annular ring radially outward of the central axis, and coupling the annular ring to the plurality of vanes. The method can further include coupling a base plate to the annular ring, the base plate having a recess formed in a radially outer surface of the base plate opposite the annular ring. The method can further include selectively and removably arranging a first collar that is cylindrical within the recess at a first rotational position therein, the first collar having a first cylindrical cavity formed therein and opening radially outwardly.
The method can further include fixedly coupling a roller pin to a radially outer surface of a second collar that is cylindrical, and selectively and removably arranging the second collar within the first cylindrical cavity of the first collar at a second rotational position therein so as to locate the roller pin at a first discrete roller pin position. A first central axis of the first cylindrical cavity is offset from a second central axis of the first collar and a third central axis of the roller pin is offset from a fourth central axis of the second collar, and the first collar is configured to be selectively arranged at a plurality of rotational positions including the first rotational position within the recess and the second collar is configured to be selectively arranged at a plurality of rotational positions including the second rotational position within the first cylindrical cavity of the first collar such that the roller pin is configured to be positioned at a plurality of distinct roller pin positions including the first discrete roller pin position each corresponding to a rotational position of the first collar and a rotational position of the second collar.
In some embodiments, the method can further include removing the first collar from the recess and reinserting the first collar in the recess at a third rotational position different than the first rotational position. In some embodiments, the method can further include removing the second collar from the first cylindrical cavity and reinserting the second collar in the first cylindrical cavity at a fourth rotational position different than the second rotational position.
Another embodiment of a vane adjustment assembly 136 that is configured to be utilized in the gas turbine engine 10 is shown in
The vane adjustment assembly 136 is configured similarly to the vane adjustment assembly 36, in particular to include a ring adjustment assembly 140 including a base plate 142, a first collar 152, a first cavity 154 formed in the first collar 152, a second collar 162, and a roller pin 170 arranged on the second collar 162. The first cavity 154 is formed eccentrically within the first collar 152. Similarly, the roller pin 170 is eccentrically arranged on the second collar 162.
As can be seen in
The ring adjustment assembly 140 differs from the ring adjustment assembly 40 described above in that the first and second collars 152, 162 do not include spline teeth. Instead, the first collar 152 is arranged within the recess 146, or cylindrical cavity 146, with an interference fit such that the first collar 152 is securely held within the recess 146 when arranged therein. Similarly, the second collar 162 is arranged within the first cylindrical cavity 154, also referred to as a second cylindrical cavity in some embodiments, with an interference fit such that the second collar 162 is securely held within the first cylindrical cavity 154 when arranged therein. The lack of spline teeth enables the allows the first and second collars 152, 162 to be arranged at an infinite number of rotational positions within the recess 146 and first cavity 154, respectively.
Another embodiment of a vane adjustment assembly 236 that is configured to be utilized in the gas turbine engine 10 is shown in
The vane adjustment assembly 236 is configured similarly to the vane adjustment assemblies 36, 136, in particular to include a ring adjustment assembly 240 including a base plate 242, a first collar 252, a first cavity 254 formed in the first collar 252, a second collar 262, and a roller pin 270 arranged on the second collar 262. The first cavity 254 is formed eccentrically within the first collar 252. Similarly, the roller pin 270 is eccentrically arranged on the second collar 262.
As can be seen in
The ring adjustment assembly 240 differs from the ring adjustment assembly 40 described above in that the first and second collars 252, 262 do not include spline teeth. Instead, the first collar 252 is arranged within the recess 246, or cylindrical cavity 246, with an interference fit such that the first collar 252 is securely held within the recess 246 when arranged therein. The lack of spline teeth enables the allows the first and second collars 252, 262 to be arranged at an infinite number of rotational positions within the recess 246 and first cavity 254, respectively.
Moreover, the inner circumferential surface 253 defining the first cavity 254 is tapered in a radial direction of the annular ring 30 such that a diameter of the first cavity 254 at a radially outermost side of the first cavity 254 is larger than a diameter of the first cavity 254 at a radially innermost side of the first cavity 254, as shown in
Another embodiment of a vane adjustment assembly 336 that is configured to be utilized in the gas turbine engine 10 is shown in
The vane adjustment assembly 336 is configured similarly to the vane adjustment assemblies 36, 136, 236, in particular to include a ring adjustment assembly 340 including a base plate 342, a first collar 352, a first cavity 354 formed in the first collar 352, a second collar 362, and a roller pin 370 arranged on the second collar 362. The first cavity 354 is formed eccentrically within the first collar 352. Similarly, the roller pin 370 is eccentrically arranged on the second collar 362. In some embodiments, the second collar 362 can extend through a lower opening of the cavity 354 if the cavity 354 is formed to not include a bottom surface.
The ring adjustment assembly 340 differs from the ring adjustment assemblies 40, 140, 240 described above in that the base plate 342 is formed as a base frame 342. In particular, as illustratively shown in
In some embodiments, the inner circumferential surface 353 defining the second cylindrical cavity 354 of the first collar 352 includes at least one first step 353S such that the inner circumferential surface 353 includes a first stepped portion 353S1 and a second stepped portion 353S2 having a smaller diameter than the first stepped portion 353S1, as shown in
Another embodiment of a vane adjustment assembly 436 that is configured to be utilized in the gas turbine engine 10 is shown in
The vane adjustment assembly 436 is configured similarly to the vane adjustment assemblies 36, 136, 236, 336 in particular to include a ring adjustment assembly 440 including a base plate 442, a first collar 452, a first cavity 454 formed in the first collar 452, a second collar 462, and a roller pin 470 arranged on the second collar 462. The first cavity 454 is formed eccentrically within the first collar 452. Similarly, the roller pin 470 is eccentrically arranged on the second collar 462. In some embodiments, the second collar 462 can extend through a lower opening of the cavity 454 if the cavity 454 is formed to not include a bottom surface.
The ring adjustment assembly 440 differs from the ring adjustment assemblies 40, 140, 240, 340 described above in that the base plate 442 is formed as a base frame 442. In particular, as illustratively shown in
In some embodiments, the base frame 442 may include a bracket 443 that is fixedly mounted on the annular ring 30, as shown in
In some embodiments, the inner circumferential surface 453 defining the second cylindrical cavity 454 of the first collar 452 includes at least one first step 453S such that the inner circumferential surface 453 includes a first stepped portion 453S1 and a second stepped portion 453S2 having a smaller diameter than the first stepped portion 453S1, as shown in
Similarly, the inner circumferential surface defining the first cylindrical cavity 446, or recess 446 in some embodiments, includes at least one third step 446S such that the inner circumferential surface includes a fifth stepped portion 446S5 and a sixth stepped portion 446S6 having a smaller diameter than the fifth stepped portion 446S5, as shown in
A method of adjusting a vane assembly of a gas turbine engine according to the present disclosure includes providing a plurality of vanes of the vane assembly, the plurality of vanes extending radially outward relative to a central axis of the gas turbine engine, arranging an annular ring radially outward of the central axis, and coupling the annular ring to the plurality of vanes. The method can further include mounting a base frame on the annular ring, the base frame including a support body extending axially away from the annular ring, the support body having a first cylindrical cavity formed therethrough that extends radially and that is offset axially from the annular ring.
The method can further include selectively and removably arranging a first collar that is cylindrical within the first cylindrical cavity at a first rotational position therein, the first collar having a first cylindrical cavity formed therein and opening radially outwardly. The method can further include fixedly coupling a roller pin to a radially outer surface of a second collar that is cylindrical, and selectively and removably arranging the second collar within the second cylindrical cavity of the first collar at a second rotational position therein so as to locate the roller pin at a first discrete roller pin position. A first central axis of the first cylindrical cavity is offset from a second central axis of the first collar and a third central axis of the roller pin is offset from a fourth central axis of the second collar, and the first collar is configured to be selectively arranged at a plurality of rotational positions including the first rotational position within the first cylindrical cavity and the second collar is configured to be selectively arranged at a plurality of rotational positions including the second rotational position within the second cylindrical cavity of the first collar such that the roller pin is configured to be positioned at a plurality of distinct roller pin positions including the first discrete roller pin position each corresponding to a rotational position of the first collar and a rotational position of the second collar.
In some embodiments, the method can further include removing the first collar from the first cylindrical cavity and reinserting the first collar in the first cylindrical cavity at a third rotational position different than the first rotational position. In some embodiments, the method can further include removing the second collar from the second cylindrical cavity and reinserting the second collar in the second cylindrical cavity at a fourth rotational position different than the second rotational position.
While the disclosure has been illustrated and described in detail in the foregoing drawings and description, the same is to be considered as exemplary and not restrictive in character, it being understood that only illustrative embodiments thereof have been shown and described and that all changes and modifications that come within the spirit of the disclosure are desired to be protected.
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