Gas turbine engines include one or more compressors for pressurizing a working medium fluid, typically ambient air, which flows through a longitudinally extending compressor flow path. Under some operating conditions, it is desirable to temporarily moderate the pressure at the discharge end of the compressor to prevent or recover from compressor stall or other aerodynamic instabilities. Pressure moderation is usually effected by opening a compressor bleed valve that diverts a portion of the pressurized fluid from the discharge end of the compressor flow path into a lower pressure region.
An exemplary compressor bleed valve system includes a moveable full hoop valve ring with a pair of ring seal members radially aligned with the bleed duct case seal seats. The compressor bleed duct includes a stationary ring having a pair of resilient seal members adhesively bonded or clamped into respective channels on longitudinally facing surfaces of the ring. A series of circumferentially distributed passages extend through the bleed duct case to join the compressor flow path to a surrounding annular chamber. The compressor bleed duct also includes a moveable valve ring with a cylindrical sleeve and a pair of seal seats radially aligned with the orifice ring seal members. A set of pins extends radially from the valve ring, and each pin includes a roller that engages a carved slot on the orifice ring. A bell crank for operating the valve ring is mounted on a bell crank support bracket by a bell crank pivot. Input and output arrays of the bell crank are connected respectively to an actuator and to the valve ring.
In operation, the actuator rotates the bell crank about the bell crank pivot so that the bell crank, in turn, drives the valve ring in a spiral motion, positioning the sleeve to cover or uncover the passages. The rollers help guide the valve ring in its spiral path. As the valve ring approaches its fully closed position, the seal members contact the seal seats, compressing them in the longitudinal direction to affect a fluid tight seal.
According to an exemplary embodiment disclosed herein, a duct assembly for venting flow from an internal portion of a gas turbine engine, has a first piece having a first duct portion extending therethrough, the first piece configured to withstanding backbone loads of the engine, the first piece having a first portion of a duct passing therethrough, and a second piece, the second piece having a second portion of the duct passing therethrough, the second portion and the first portion aligning, the second piece constructed of a lighter material than the first piece.
In any of the previous embodiments, the first piece is constructed of titanium.
In any of the previous embodiments, the second piece is constructed of aluminum.
In any of the previous embodiments, the aluminum is cast aluminum.
In any of the previous embodiments, the first piece has a plurality of first portions and the second piece has a plurality of second portions.
In any of the previous embodiments, the second portions are separated by ligaments that minimize losses flowing through the first portions and aligned second portions.
In any of the previous embodiments, the ligaments are have an airfoil shape.
In any of the previous embodiments, a seal is disposed between the first piece and the second piece.
In any of the previous embodiments, the seal is disposed in a groove in one of the first piece and the second piece.
In any of the previous embodiments, a flange extends axially from one of the first piece and the second piece and a bracket extends radially from the flange to engage an other of the first piece and the second piece.
In any of the previous embodiments, the bracket engages a side of the other of the first piece and the second piece.
In any of the previous embodiments, the first piece forms a radially outer wall of a compressor section of the engine.
In any of the previous embodiments, the first piece attaches to another portion of a radially outer wall of the compressor section,
In any of the previous embodiments, a radially extending flange extends from the second portion of the duct for engaging a seal.
In any of the previous embodiments, a platform is disposed on said first portion of said duct, said platform configured to support a ring assembly thereupon.
In any of the previous embodiments, a mount is disposed on a radially outer surface of said first piece for mounting a bell crank thereupon.
According to an exemplary embodiment disclosed herein, a method for minimizing weight of a duct assembly includes the steps of selecting a first material to withstand engine backbone loads, selecting a second material that is lighter than the first material, forming aligning ducts in the first material and in the second material, and mating the first material and the second material to form duct assembly.
In any of the previous embodiments, the method includes aligning the second material radially outwardly from the first material such that the ducts align.
In any of the previous embodiments, the method includes creating ligaments that are airfoil shaped between ducts in the first material.
In any of the previous embodiments, the method includes casting the ligaments of the second material.
The various features and advantages of the disclosed examples will become apparent to those skilled in the art from the following detailed description. The drawings that accompany the detailed description can be briefly described as follows.
Referring now to
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The inner casing 80 has a body 110 having a central area 115 having a first land 120 on a top portion 125 of the body 110. The top portion 125 has a groove 130 in which an o-ring 135 is disposed to act as a seal to minimize air from escaping between the duct portions 95, 100. Bolt hole 140 is disposed in a side portion 145 of the body 110 for attaching the outer case 85 to the inner case 80 by means of a bolt 150. The inner casing 80 has an aft extension 155 having an axial attachment hole 160 to attach to an adjacent core segment 165 (see
On a radially outer surface of the body 110, a platform 190, which supports the bleed valve 60, is disposed thereon. There are a plurality of platforms disposed circumferentially about the body 110 to support the valve 60. The platforms has a cylindrical top 195 that has a flat cross-section and is covered by a low wear material 200 that is somewhat lubricious to allow the bleed valve 60 to slide thereon without snagging.
The outer case 85 has a body 205 having an aft flange 210 depending radially inwardly from the body 205. The aft flange 210 has a hole 215 aligning with bolt hole 140 through which bolt 150 extends into the bolt hole 140 to attach the outer case 85 to the inner case 80. The outer case body 205 has a flange 220 extending radially outward to mate with the bleed valve 60 as will be discussed infra. The body 205 also has a fore side 225 that mates with the bleed valve 60 as will be discussed infra. The body 205 has a second land 230 that mates with the first land 120 when the bolt 150 is inserted into hole 140. When the bolt 150 is tightened, the first land 120 and the second land 230 secure the O-ring 135 to minimize any air leakage between the bolts. The o-ring 135 gets compressed when the case halves are installed.
The airfoils 100, or ligaments disposed between ducts 90 are shaped to direct the flow of air flowing through the duct 90 to enhance flow with minimal losses therethrough so that the air siphoned from the compressor section 45 may be used efficiency downstream of the ducts 90. The outer case 85 is aluminum to allow more complex flow patterns of the duct second portion 100 to be machined or formed to maximize efficiency of the air flowing therethrough. The first portion 95 in the inner case 80 and the second portion 100 in the outer case 85 are smoothed to minimize losses. Furthermore, the outer case 85 is made of aluminum or the like to save weight and the inner case is made of titanium to improve the capability of the bleed duct assembly 65 to handle engine backbone loads. Because the inner case handles the backbone loads, the outer case 85 may be made of aluminum where weight may be saved. Because the outer case 85 is cast, more shaped airfoils may be used to reduce aerodynamic losses and reduce backflow upon the compressor section 45.
A user would choose a first material as an inner case 80 to withstand the backbone loads of the engine 10, then choose a lighter material as an outer case 85 to form a lighter bleed duct assembly 65. The user would then form the duct 90 for instance by casting the outer case 85 and forging the inner case 80 and then join the two segments as mentioned hereinabove.
Referring now to
The aft bell crank 240 has a body 255 from which brackets 260 extend circumferentially and radially inwardly therefrom. A rotation pin 265 extends through the body 255 to hold a bell crank 280. The body 255 has a flange 270 extending radially outwardly therefrom. The upper flange 270 has holes 275 passing axially therethrough for joining with the bridge arm 250. The bell crank 280 is seated within the body 255 and has an upper arm 285 for attaching to the fore connecting link 245 and a lower arm 290 disposed radially inwardly from the upper arm 285 attaching to an aft connecting link 295. The aft connecting link 295 attaches to an actuator (not shown).
The brackets 260 have a base 300 and webs 305 that attach to the aft bell crank body 255. The brackets 300 sit upon land 310 on the stationary inner case 80. A pin 315 extends radially outwardly from the land 210 for insertion into the locator hole 320 in the base 300. Bolt 323 connects the bracket 260 to the inner case 80.
The fore bell crank assembly 235 has a body 325. A pin 330 extends through clevis 335 to anchor crank 337 therein (See
The bridge arm 250 has a key-like shape having a flat triangular section 390 that has openings 394 for mating with the bolt holes 370 and an aperture 397 for mating with the pin 365 to attach the bridge arm 385 to the fore bell crank assembly. The bridge arm 250 also has a shank 395 which narrows axially and expands radially from the triangular section 390. A t-shaped assembly 400 is formed by ears 405 that extend circumferentially from an end 407 of the shank 395. The ears have openings 410 through which fasteners 415 extend to mate with the holes 275 in the upper flange 270 of the aft bell crank 240. The openings 394 and aperture 397 may be oversized to allow for circumferential misalignment.
The webs 305 of the aft bell crank assembly 240 are designed to flex during thermal loading while providing stiffness for operating loads. The bridge arm 250 limits deflection of the cantilevered fore bell crank assembly 235 and aft bell crank assembly 240 and provides more stiffness to the linkage assembly 75. Shims 417 are placed between the t-section 400 and the upper flange 270 to eliminate axial tolerance gaps during assembly.
Because the area to mount the brackets 260 to the inner case 80 is limited, the required stiffness and deflection of the aft bell crank assembly 240 is provided by providing the bridge arm 250 between the aft bell crank 240 and the fore bell crank assembly 235, which is attached to the flange of the adjacent core segment 165. The bridge arm 250 is designed not to buckle or deflect during excessively unloading. The aft brackets 260 are more flexible to allow for controlled deflection of the fore bell crank assembly 235 and the aft bell crank assembly 240 caused by thermal growth of the inner case 80.
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A shaft 485 extends upwardly from the flat portion 480 at periodical positions around the seal 455 to attach the seal to the seal holders 435, 445. A shank 490 of a rivet 497 (or other fastener) extends through a center of the shaft 485. The rivet 495 has a head 500, a tail 505, and a bottom 515. The bottom 515 fits within a recess 510 in each seal holder 435, 445. As can be seen in
The preceding description is exemplary rather than limiting in nature. Variations and modifications to the disclosed examples may become apparent to those skilled in the art that do not necessarily depart from the essence of this disclosure. The scope of legal protection given to this disclosure can only be determined by studying the following claims.