US3313475A - Mounting of hardware on axial flow compressor casings - Google Patents

Mounting of hardware on axial flow compressor casings Download PDF

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Publication number
US3313475A
US3313475A US475768A US47576865A US3313475A US 3313475 A US3313475 A US 3313475A US 475768 A US475768 A US 475768A US 47576865 A US47576865 A US 47576865A US 3313475 A US3313475 A US 3313475A
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US
United States
Prior art keywords
casing
mounting
hardware
compressor
bushing
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US475768A
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English (en)
Inventor
Jr Rylance H Bostock
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US475768A priority Critical patent/US3313475A/en
Priority to GB27598/66A priority patent/GB1120960A/en
Priority to FR68078A priority patent/FR1485370A/fr
Priority to DE19661476792 priority patent/DE1476792A1/de
Priority to BE684856D priority patent/BE684856A/xx
Application granted granted Critical
Publication of US3313475A publication Critical patent/US3313475A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps

Definitions

  • the present invention relates to improvements in axial flow compressors used in gas turbine engines and more particularly to improvements in mounting various items commonly referred to as hardware on casings of such compressors.
  • Titanium uniquely provides high structural strength with a minimum weight, however, its use also introduces serious problems in the mounting of various items thereon, including so-called hardware items such as pipe line supports and actuators and other controls and accessories components normally associated with or secured to the compressor casings.
  • the outer surface of the casing has, to a large extent, become inaccessible for the provision of conventional mounting pads.
  • This type of compressor employs stator blades which are pivotally adjusted about radial axes. Such adjustment is obtained by providing lever arms secured to each of the stator blades and overlying the outer casing surface. These lever arms and the control elements therefor are so closely spaced that little available room is left for mounting purposes.
  • One object of the invention is to overcome the problems of mounting hardware items on axial flow compressors having casings formed of titanium or like material which are difiicult or impractical to machine.
  • Another object of the invention is to provide means for mounting hardware components on axial flow compressor casings of the type having large areas of the casing surface overlaid by stator adjusting elements.
  • Another and more specific object of the invention is to provide an improved mounting bracket for axial flow compressor casings which will give a greater versatility of design with a minimum of cost and weight.
  • the present invention is characterized by the provision of an improved bracket construction for use in combination with an axial flow compressor comprising an outer casing advantageously formed of titanium or equivalent metal.
  • the compressor itself preferably comprises a plurality of stator blades which are secured at one end by a bushing projecting through an unthreaded hole in the casing, with a nut threaded over the exterior of the bushing to clamp the bushing in place and thus provide a fixed journal on the casing wall for the stator.
  • Levers attached to the outer ends of the stator overlie the casing and are connected to' control means for adjusting the angular position of the stator levers to thereby obtain maximum performance of the compressor itself.
  • the stator blades are usually arranged in axially spaced rows along the length of the casing with each row normally functioning in combination with a row of rotor blades to form a compressor stage.
  • the mounting bracket cooperating with this construction comprises one or more bridge portions which may extend from one stator to another.
  • the opposite ends of each bridge portion are in the form of feet, apertured and telescoped over the stator mounting bushings.
  • the nuts which secure the bushings in place are also employed for the dual purpose of securing the mounting bracket feet on the casing.
  • the bridge portion of the bracket is then provided with mounting means for securing hardware thereto.
  • FIGURE 1 is an elevation illustrating in outline fashion a gas turbine engine of the type in which the present invention is advantageously embodied;
  • FIGURE 2 is an enlarged fragmentary elevation of a portion of the axial flow compressor seen in FIGURE 1;
  • FIGURE 3 is a section taken on line IIIIII in FIG- URE 2;
  • FIGURE 4 is a section, on an enlarged scale, taken on line IVIV in FIGURE 2;
  • FIGURE 5 is a perspective view of a bracket seen in FIGURE 2.
  • FIGURE 6 is a perspective view of an alternate embodiment of the invention.
  • FIGURE 1 illustrates a gas turbine engine 10 comprising an axial flow compressor 12 which ingests air and compresses it to the desired density to properly support combustion of fuel in a combustor section 14.
  • the combustion gases pass through a turbine stage 16 which provides the driving force for the rotor (not shown) of the axial flow compressor 12.
  • the cornbustion gases are then discharged through a tail section 18 and then through an afterburner section 24).
  • the axial flow compressor 12 comprises an outer casing 22 which is usually formed by two semi-cylindrical shells.
  • the compressor 12 further comprises a plurality of stators 24- which are arranged in circumferential rows spaced along the length of the casing 22 (see also FIGURE 4).
  • the stators 24 cooperate with rotor blades within the casing 22 with each pair of rotor and stator rows forming a compressor stage.
  • FIGURES 2 through 3 the stators are pivotally adjustable about axes extending radially of the compressor.
  • FIGURES 2 through 3 the outer ends of the stators are journaled on the casing 22 and have secured thereto a lever 26 which projects into overlying relation with the outer surface of the casing 22.
  • the several levers 26 of each stage are interconnected by an actuating ring 28 (FIGURE 1).
  • These actuating rings are in turn connected to a common control lever (two may be employed if desired) that is pivotally mounted at 32 and displaced by an actuator 34 in order to simultaneously adjust the stators of each stage connected thereto to provide optimum operation of the axial flow compressor.
  • Such stator adjustment apparatus is more particularly described in co-pending US. patent application Ser. No. 462,688 filed June 9, 1965 and assigned to the same assignee as the present application.
  • a bracket 36 (FIGURES 2-5) which will now be described in detail.
  • the bracket 36 is of generally triangular outline forming a bridge portion 38, having feet 46 at its opposite ends.
  • An aperture 42 is provided in each of the feet 46 and the upper surface thereof is provided with a counterbore 44 which may be either machined or otherwise formed.
  • each stator mounting means comprises a bushing 46 having a flange 48 at its lower end.
  • the casing itself is formed with a hole 56 through which the bushing 46 is projected with the flange 48 preferably engaging a counterbored surface 52 on the interior of the casing 22.
  • the lower surfaces of the feet 40 engage counterbore-d surfaces 54 formed on the outer surface of the casing 22 marginally of the holes 50.
  • a nut 56 is threaded over the upper end of the bushing 46 and clamps against the counterbored surface 44 to draw the flange 48 against the counterbored surface 52 thereby firmly securing the insert 46 and one leg 40 of the bracket to the compressor casing.
  • the opposite end of the bracket 36 is secured to the casing 22 in the same fashion by being telescoped over the adjacent bushing 48 in the same row of stators as indicated in FIGURES 2 and 3.
  • the bridge portion 38 of the bracket 36 is provided with hardware securing means which advantageously take the form of a steel insert 60 pressed-fitted into the central portion of the bridge portion 38 against a lip 61.
  • the bracket 36 is preferably formed of aluminum and the steel insert 60 is employed to provide threads of sufficient strength.
  • a screw 62 is threaded into the insert 60 to clamp a holder 64 thereon, the holder providing means for supporting a tube 1 running along the length or tangentially of the compressor casing 22.
  • the bracket 36 is of the triangular configuration illustrated wherein the bridge portion 38 tapers down to a minimum height at the feet 40 and its undersurface is relieved so that bearing surfaces on the feet need be machined only at the points of engagement with the counterbores 54 formed on the casing 12 marginally of the holes 50. It is also advantageous that the height of the bridge be below the level of the outer ends of the stators to minimize the over-all cross sectional outline of the compressor. However, it would also be possible that the bridge portion be sufficiently high to span over one or more of the stators. Likewise if it is desired to secure a larger piece of hardware to the compressor casing, the alternate embodiment of FIGURE 6 may be employed wherein two bridging portions 38 are provided and are joined by a common foot portion 40. In FIGURE 6 corresponding portions are identified by like reference characters without specific description.
  • a mounting bracket used in combination with an axial flow compressor of the type comprising,
  • stator blades arranged in circumferential rows along the length of the compressor
  • said bracket comprising,
  • each foot being apertured and telscoped over a stator mounting bushing, common means securing each foot portion and the bushing over which it is telescoped to said casing, and
  • clamping means carried by said bridge portion for the securing of hardware thereto to thus mount the hardware on the casing.
  • a mounting bracket used in combination with an axial flow compressor of the type comprising,
  • stator blades arranged in circumferential rows along the length of the compressor
  • said casing having holes therethrough and a bushing projected through said holes to provide means for mounting the outboard end of each stator blade, said bracket comprising a bridge portion terminating at each end in a foot,
  • each foot being apertured and telescoped over a stator mounting bushing
  • each bushing over which a foot is telescoped having a flange engaging the inner surface of said casing and a nut threaded over the outer end thereof and engaging said foot to provide common means for securing each foot and the bushing over which it is telescoped to said casing, and
  • clamping means carried by said bridge portion for the securing of hardware thereto to thus mount the hardware on the casing.
  • a mounting bracket used in combination with an axial flow compressor of the type comprising,
  • stator blades arranged in circumferential rows along the length of the compressor
  • said casing having holes therethrough and bushings respectively projected through said holes to provide journal means for mounting the outboard ends of the stator blades
  • bracket comprising a bridge portion of generally triangular outline, terminating at each end in a foot, each foot being apertured and telescoped over a stator mounting journal bushing,
  • each bushing over which a foot is telescoped having a flange at its inner end engaging the inner surface of said casing, the inner surface of said casing being counterbored to provide an accurate bearing surface marginally of said hole for said flange a nut threaded over the outer end of said bushing and engaging the counterbored surface of said foot to provide common means for securing each foot and the bushing over which it is telescoped to said casing, and
  • clamping means carried by said bridge portion for the securing of hardware thereto to thus mount the hardware on the casing.
  • a mounting bracket used in combination with an axial flow compressor of the type comprising,
  • stator blades arranged in circumferential rows along the length of the compressor
  • said casing having holes therethrough and bushings resaid bracket comprising a bridge portion of generally triangular outline terminating at each end in a foot, 5
  • each foot being apertured and the two feet being telescoped over the stator mounting bushings of adjacent stators in one of said rows,
  • each bushing over which a foot is telescoped having a flange at its inner end, engaging the inner surface of said casing, the inner surface of said casing so engaged being counterbored to provide an accurate 1 bearing surface marginally of said hole for said flange, the opposed outer surface of said casing also being counterbored to provide an accurate bearing surface marginally of said hole for engagement by said feet, a nut threaded over the outer end of said bushing and engaging the counterbored surface of said foot to provide common means for securing each foot and the bushing over which it is telescoped to said casing,
  • a threaded insert secured to the central portion of said bridge portion to provide clamping means for securing of hardware thereto to thus mount the hardware on the casing.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US475768A 1965-07-29 1965-07-29 Mounting of hardware on axial flow compressor casings Expired - Lifetime US3313475A (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US475768A US3313475A (en) 1965-07-29 1965-07-29 Mounting of hardware on axial flow compressor casings
GB27598/66A GB1120960A (en) 1965-07-29 1966-06-21 Improvements in mounting of hardware on axial flow compressor casings
FR68078A FR1485370A (fr) 1965-07-29 1966-07-04 Dispositif de montage des accessoires sur le carter d'un compresseur à écoulement axial
DE19661476792 DE1476792A1 (de) 1965-07-29 1966-07-21 Vorrichtung zur Befestigung von Metallteilen oder -beschlaegen an Gehaeusen von Axialstroemungskompressoren
BE684856D BE684856A (cs) 1965-07-29 1966-07-29

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US475768A US3313475A (en) 1965-07-29 1965-07-29 Mounting of hardware on axial flow compressor casings

Publications (1)

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US3313475A true US3313475A (en) 1967-04-11

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US475768A Expired - Lifetime US3313475A (en) 1965-07-29 1965-07-29 Mounting of hardware on axial flow compressor casings

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US (1) US3313475A (cs)
BE (1) BE684856A (cs)
DE (1) DE1476792A1 (cs)
GB (1) GB1120960A (cs)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11149580B2 (en) * 2019-07-25 2021-10-19 Raytheon Technologies Corporation Self retained linkage and system including the self retained linkage for a gas turbine engine
CN114714081A (zh) * 2022-04-19 2022-07-08 中国航发动力股份有限公司 一种分解前轴承座机匣的工装及方法

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4309637A1 (de) * 1993-03-25 1994-09-29 Abb Management Ag Radialdurchströmte Abgasturboladerturbine
CN115008170B (zh) * 2022-06-24 2023-09-26 江西中发天信航空发动机科技有限公司 联动式外机匣数控分离器

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1111358A (fr) * 1954-02-04 1956-02-27 Canadian Patents Dev Segments annulaires d'enveloppe réglables pour turbines à gaz
US2819732A (en) * 1954-07-14 1958-01-14 Thompson Prod Inc Variable area turbine entrance nozzle
US2933235A (en) * 1955-01-11 1960-04-19 Gen Electric Variable stator compressor
US3079128A (en) * 1961-01-23 1963-02-26 Burge Joseph Sealing and securing means for turbomachine blading

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1111358A (fr) * 1954-02-04 1956-02-27 Canadian Patents Dev Segments annulaires d'enveloppe réglables pour turbines à gaz
US2819732A (en) * 1954-07-14 1958-01-14 Thompson Prod Inc Variable area turbine entrance nozzle
US2933235A (en) * 1955-01-11 1960-04-19 Gen Electric Variable stator compressor
US3079128A (en) * 1961-01-23 1963-02-26 Burge Joseph Sealing and securing means for turbomachine blading

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11149580B2 (en) * 2019-07-25 2021-10-19 Raytheon Technologies Corporation Self retained linkage and system including the self retained linkage for a gas turbine engine
CN114714081A (zh) * 2022-04-19 2022-07-08 中国航发动力股份有限公司 一种分解前轴承座机匣的工装及方法
CN114714081B (zh) * 2022-04-19 2023-01-31 中国航发动力股份有限公司 一种分解前轴承座机匣的分解方法

Also Published As

Publication number Publication date
BE684856A (cs) 1967-01-03
GB1120960A (en) 1968-07-24
DE1476792A1 (de) 1969-12-11

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