US3647312A - Mounting of stator blades in axial compressors - Google Patents

Mounting of stator blades in axial compressors Download PDF

Info

Publication number
US3647312A
US3647312A US11948A US3647312DA US3647312A US 3647312 A US3647312 A US 3647312A US 11948 A US11948 A US 11948A US 3647312D A US3647312D A US 3647312DA US 3647312 A US3647312 A US 3647312A
Authority
US
United States
Prior art keywords
ring
blades
stator
gear
compressor
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
US11948A
Other languages
English (en)
Inventor
Zbynek Janc
Vaclav Kadera
Josef Novotny
Adolf Nemec
Jiri Penkava
Miloslav Vondruska
Zdenek Vitkovec
Jiri Feierfeil
Vlastimil Svoboda
Dusan Misarek
Miroslav Futera
Katerina Nacovska
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.)
CKD Praha DIZ AS
CKD Praha Oborovy Podnik
Original Assignee
CKD Praha DIZ AS
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 CKD Praha DIZ AS filed Critical CKD Praha DIZ AS
Application granted granted Critical
Publication of US3647312A publication Critical patent/US3647312A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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
    • 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

Definitions

  • ABSTRACT A compressor in which the blades of the stator are mounted in [21] Appl.No.: 11,948
  • each ring is provided with an associated second annular ring in which is located link means extending into engagement with each of the blades mounted on the first ring.
  • the link 415/149 means are arranged to swivel the blades about their axes.
  • 27/00 Means are provided for oscillating the second ring member to .415/148, 149, 150, l5i, 160, actuate the link means [5i] [58] FieldofSearch.................
  • Conventional compressors comprise a rotor and a stator spaced therefrom to form an annular axial passage.
  • the stator and rotor both are provided with blades extending radially into the passage.
  • the stator blades are conventionally mounted so that their pitch or angular position about its own longitudinal (or radially directed) axis may be varied. It has been the custom to provide a control drum between the outer surface of the stator and the housing or shell of the compressor, which by appropriate linkage is connected to each of the blades.
  • the control drum is movable either rotatably about the stator or axially therealong and when so activated adjusts to the position of the blades.
  • the prior art devices greatly enlarge the diameter of the compressor and add great weight to it. Furthermore, such constructions are difficult to seal and, consequently, the flow passage is open to contaminating influences and loss of gas pressure.
  • the prior art has sought to overcome these disadvantages by the use of complex sealing and structural elements which only tend to increase size, weight and the complexity of the compressor.
  • the blades of the stator are mounted in circular rows in a plurality of abutting axially aligned ring-shaped members secured in a recess in the inner wall of the stator, each ring is provided with an associated second annular ring in which is located link means extending into engagement with each of the blades mounted on the first ring.
  • the link means are arranged to swivel the blades about their axes.
  • Means are provided for oscillating the second ring member to actuate the link means.
  • adjacent annular rings are grouped together so that their blades may be pivoted conjointly.
  • FIG. I shows a partial view of a compressor sectionalized along two longitudinal planes conforming to lines I-I and I I of FIG. 2 to show the internal structure;
  • FIG. 2 is a cross section; of the compressor of FIG. 1 sectionalized planes II-II and IIII to show the internal structure;
  • FIG. 3 is an enlarged detailed view of the portions shown in FIG. 2;
  • FIG. 4 is an enlarged detailed view of the portions shown in FIG. 1;
  • FIG. 5 is a schematic representation of a compressor
  • FIG. 6 is a diagrammatic view of the swivel adjustment of the blades shown in FIG. 1.
  • the compressor briefly comprises a large drum type rotor 1 having many rows of dynamically shaped blades 3 extending outwardly from it in a radial direction.
  • the rotor l is surrounded by a fixed stator 2, conventionally formed in two casing parts, and furnished with a number of rows of blades 4 similar to blades 3, that extend inwardly between the rows of blades on the rotor 1.
  • the two casing parts fit together about the rotor to form an annular passage 5, into which the blades 3 and 4 extend and through which gas flows as it is compressed.
  • the blades are supported in circular, axially arranged rows about the axis of the compressor.
  • Each row comprises an annular ring support 6, as seen in FIG. 2.
  • a plurality of ring supports 6 are secured in abutting axial relationship within a recess 7 formed in the inner wall of the stator 2 (FIG. 1).
  • the blades 4 extend radially into the passage 5 in a predetermined array in association with the blades 3 of the rotor.
  • Each of the blades 4 are individually mounted so as to swivel about their own longitudinal axes X and are arranged in a suitable radial opening 9 in the support 6, which has an L- shaped cross section with a horizontal or axially extending cylindrical portion (FIG. 1) and a vertical or radial rib (FIG. 2).
  • Each support ring 6 is also divided into two horizontal parts to facilitate assembly of a second annular ring 8 in the space formed therebetween.
  • the second ring 8 is coaxially aligned with the support ring 6 and is adapted to control the movement of each blade.
  • the outer surface of each support is linear with the inner wall of the stator 2 so as to cooperate in defining the wall of passage 5.
  • each support 6 has a plurality of radial openings 9 into each of which is slidably fit the shank or journal end 10 of one of the blades 4, which is retained by a ring washer 10' located in an annular groove at its end.
  • the contacting area between the support ring 6 and the control ring 8 is provided with corresponding grooves 11 in which ball bearings 12 or the like are situated.
  • the second ring 8 or control ring constitutes a part of the swivel actuating mechanism for each blade and is provided with a gear means comprising a segment 13 which is in engagement with a pinion 14 secured to the end of a shaft 15.
  • the shaft 15 is rotatably supported in bearings 16 in a channel 15 formed in the body ofthe stator 2 (FIG. 4).
  • the control ring 8 in association with each blade 4 is provided with link means for angularly positioning the blade.
  • the ring 8 is formed with a radial bore 17 in which is secured a bolt 18 having a bifurcated or forked end, extending over an axially arranged pin 19 which extends from the sleeve 8 through the support 6 into a cross drilled hole in the shank or journaled end 10 of the blade.
  • the engaging portions of the bifurcated bolt 18 and the pin 19 are flat and substantially rectangular as seen in FIG. 4, so that movement of the bolt will be positively translated to the pin. It will then be apparent that on rotation of the shaft 15, the rotary movement is translated by gear segment 13 into oscillation of the control ring 8, which in turn causes, through bolt 18 and pin 19, the angular adjustment of the blade 4.
  • the shaft 15 may be manually activated by suitable linkages connected to the control panel or booth of the apparatus.
  • the shaft 15 is provided with a servomotor 29, which may be remotely activated.
  • the shaft 15 may be activated by an operator, or in response to an automatic throttle, speed or pressure control.
  • the supports 6 divide the entire length of the recess 7 into a series of partial ring shaped chambers sealed one from another by rubber O-rings 26 and 27 located in suitable grooves on the front wall and the outer edge respectively of the rib of support 6.
  • sealing rings 28 are provided about the bearings 16 of the shaft 15. These sealing means, prevent the escape of air from within the passage even though the interior of the support 6 and sleeve 8 are open to it. Because the support and sleeve are open to the passage 5, the gas pressure within these members is equal to that in the passage so that swinging of the blade 4 is not effected by it.
  • the support 6 with stator blades 4, the control sleeve 8 and shaft 15, etc. form an aggregate stator gridunit.
  • Each grid unit may be made with varying or different parameters so that their arrangement about the stator can be predetermined and preselected to suit certain selected and desired operating criteria.
  • certain blades may be made to swing or swivel on manual command, while others may be made to move as a function of the degree of gas compression and certain blades may be caused to swing in one direction while others swing in another.
  • the construction does not increase the size or weight of the compressor but utilizes the structure of the stator itself to house the swivel adjustment mechanism.
  • the form of the rings effectively seals the flow passage preventing loss of power and contamination of the gas. Further, the rings provide a smooth inner surface for the gas flow.
  • Apparatus for adjusting the position of stator blades in an axial flow compressor comprising a first annular ring secured within a recess in the inner wall of said stator, a plurality of blades extending radially into said passage, a
  • link means connecting each of said blades to said second ring, said link means comprises a pin extending axially into engagement with shank of said blade, and a radial bolt located in said second ring and having a bifurcated end engaging with a mating portion form on said pin, said link means arranged to swivel said blades about their longitudinal axes on rotation of said second ring, means for selectively oscillating said second ring about the axis of said compressor whereby said oscillation swivels said blad to a predetermined adjustment.
  • the apparatus according to claim 1 including a gear segment secured to said second ring, a pinion secured to an axial shaft and meshing with said segment, and motion means for selectively rotating said shaft.
  • the apparatus according to claim 2 including bearing means for rotatably supporting said second ring within said first ring.
  • Apparatus for adjusting the position of stator blades in an axial flow compressor comprising a plurality of first annular ring members secured in abutting axial relation within a recess in the inner wall of said stator, a plurality of individual blades extending from each of said first ring members radially into said passage, each of said blades having a shank rotatably journaled in said first ring member, a second ring member rotatably mounted within each of said first ring members, each of said second ring members having in association with each of the blades of said first ring member a pin extending into axial engagement with the shank of said blade, and a bolt secured in a radial bore engaging said pin for conjoint movement therewith, gear means for oscillating each of said second ring members, means for joining selected adjacent gear means to form jointly oscillating groups of second ring members,
  • said gear means comprises a gear segment mounted on said second ring member and a pinion gear mounted on a shaft, said shaft being common for each of said second ring members in each associated group, said shaft being connected to said motive means.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US11948A 1969-02-20 1970-02-17 Mounting of stator blades in axial compressors Expired - Lifetime US3647312A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CS120669 1969-02-20

Publications (1)

Publication Number Publication Date
US3647312A true US3647312A (en) 1972-03-07

Family

ID=5345873

Family Applications (1)

Application Number Title Priority Date Filing Date
US11948A Expired - Lifetime US3647312A (en) 1969-02-20 1970-02-17 Mounting of stator blades in axial compressors

Country Status (5)

Country Link
US (1) US3647312A (de)
CH (1) CH510202A (de)
DE (1) DE2005536B2 (de)
GB (1) GB1259739A (de)
SE (1) SE359148B (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3736070A (en) * 1971-06-22 1973-05-29 Curtiss Wright Corp Variable stator blade assembly for axial flow, fluid expansion engine
CN102410251A (zh) * 2010-08-31 2012-04-11 通用电气公司 用于压缩机进口导向轮叶的翼型件形状
BE1026816B1 (fr) * 2018-11-29 2020-07-01 Safran Aero Boosters Sa Système de calage variable d’aubes d’un étage statorique d’un compresseur d’une turbomachine d’aéronef

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2698405B1 (fr) * 1992-11-25 1994-12-23 Snecma Turbomachine à plusieurs étages d'aubes de stator à orientation variable.
GB201202383D0 (en) 2012-02-13 2012-03-28 Rolls Royce Plc A unison ring gear assembly

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2305311A (en) * 1937-07-07 1942-12-15 Jendrassik George Gas turbine plant equipped with regulating apparatus
GB621175A (en) * 1946-11-16 1949-04-05 Power Jets Res & Dev Ltd Improvements in or relating to stator blading of compressors and like machines
US3013771A (en) * 1960-10-18 1961-12-19 Chrysler Corp Adjustable nozzles for gas turbine engine

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2305311A (en) * 1937-07-07 1942-12-15 Jendrassik George Gas turbine plant equipped with regulating apparatus
GB621175A (en) * 1946-11-16 1949-04-05 Power Jets Res & Dev Ltd Improvements in or relating to stator blading of compressors and like machines
US3013771A (en) * 1960-10-18 1961-12-19 Chrysler Corp Adjustable nozzles for gas turbine engine

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3736070A (en) * 1971-06-22 1973-05-29 Curtiss Wright Corp Variable stator blade assembly for axial flow, fluid expansion engine
CN102410251A (zh) * 2010-08-31 2012-04-11 通用电气公司 用于压缩机进口导向轮叶的翼型件形状
BE1026816B1 (fr) * 2018-11-29 2020-07-01 Safran Aero Boosters Sa Système de calage variable d’aubes d’un étage statorique d’un compresseur d’une turbomachine d’aéronef

Also Published As

Publication number Publication date
SE359148B (de) 1973-08-20
GB1259739A (en) 1972-01-12
CH510202A (de) 1971-07-15
DE2005536B2 (de) 1972-05-04
DE2005536A1 (de) 1970-09-10

Similar Documents

Publication Publication Date Title
US4950129A (en) Variable inlet guide vanes for an axial flow compressor
JPS6137441B2 (de)
US9617922B2 (en) Jet engine actuation system
US3647312A (en) Mounting of stator blades in axial compressors
US4403913A (en) Guide blade arrangement for adjustable guide blades
GB1178650A (en) Improvements in Variable Geometry Axial Flow Compressors
US3295827A (en) Variable configuration blade
US2842305A (en) Compressor stator assembly
CN108757509B (zh) 一种燃气轮机低压压气机结构
US2823700A (en) Fluid flow control apparatus
US3030006A (en) Circumferential bleed valve
JP6846987B2 (ja) 回転揺動試験機
US2338420A (en) Arrangement for adjusting the blades of opposite rotating air propellers
US3904309A (en) Variable angle turbine nozzle actuating mechanism
US3318513A (en) Variable vane ring
US2978914A (en) Ball bearing sealed rotation transmission device
US2495434A (en) Variable pitch propeller
US3392909A (en) Vane positioning actuator
US3274836A (en) Rotary dampers
US2256055A (en) Oscillating device
US3360240A (en) Vane operating mechanism
US4132503A (en) Variable-pitch propeller
US2147761A (en) Fluid hoist
US4534705A (en) Horizontal-shaft wind turbine with few blades
SU1330332A1 (ru) Регулируемый сопловой аппарат турбомашины