US2543355A - Stator for axial compressors - Google Patents

Stator for axial compressors Download PDF

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Publication number
US2543355A
US2543355A US7488A US748848A US2543355A US 2543355 A US2543355 A US 2543355A US 7488 A US7488 A US 7488A US 748848 A US748848 A US 748848A US 2543355 A US2543355 A US 2543355A
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US
United States
Prior art keywords
webs
casing
stator
blade
platforms
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
US7488A
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English (en)
Inventor
Davis Christopher Ainsworth
Bill John Henry
Morley Frederick Willia Walton
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.)
Rolls Royce PLC
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Rolls Royce PLC
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Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
Application granted granted Critical
Publication of US2543355A publication Critical patent/US2543355A/en
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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
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • This invention relates to axial compressors, such as are for example used in gas-turbine engines, and has for an object to provide an improved construction of stator blade and stator casing for axial compressors which have advantages from the point of View of lightness, which is important in compressors used in aircraft power plants, and of ease of manufacture and assembly.
  • an axial-flow compressor stator assembly comprises a stator casing havin a relatively thin wall, a plurality of axially-spaced main internal reinforcing webs each main web extending circumferentially around and projecting radially inwardly from the wall and each main web being formed with axially-spaced outwardly facing abutment surfaces curved about the axis of said casing, and a plurality of intermediate internal reinforcing webs there being at least one intermediate web between each pair of said main webs, each said intermediate web extending circumferentially around and projectin radially inwardly from said wall and being formed with an inwardly facing abutment surface curved about the axis of said casing; and a plurality of stages of stator blading, each stage of stator blading comprising a plurality of blades in circumferential assembly supported and located by a pair of main webs and at least one intermediate web, the blades being formed with axially and circumferentially extending blade
  • outwardly-facing abutment surfaces of the blade platforms are formed on ribs projecting radially outwardly from the outer surfaces of the platforms and having an axial dimension less than the axial dimension of the platforms.
  • the main webs be formed with axially and circumferentially extending flanges having outwardly-facing abutment surfaces of the main webs formed at their axially-spaced edges, and that the inner surfaces of the main webs and platforms be arranged to provide a smooth continuous surface for the outer wall of the working fluid passage through the compressor.
  • the webs and wall are at substantially the same temperature so that circumferential thermal stresses due to the provision of reinforcing webs are avoided. Further since the wall of the casing is thin and the reinforcing webs also provide the means for retainin the'blades, the overall weight can be reduced as compared with a casing having external strengthening webs. Furthermore, the
  • .external surface can be substantially smoothwhich is an advantage from the point of view of cleanliness and appearance.
  • the compressor stator comprises a stator-casing formed in two partslfi and ll and a number of stages of compressor stator-blades 12 which are secured in the casing by their root-platforms l3.
  • the platform [3 of each blade is of substantially rectangular formand is located at the outer end of the blade so that the latter projects radially inwards from the compressor casing.
  • the wall I4 of the compressor casing is of rela tively thin section and is provided internally with continuous, circumferential, radially-projecting strengthening webs l5, l6 so that the external surface of the casing is substantially free 'from projections and presents a clean appearance.
  • the webs I5 which alternate with webs [6, have a greater radial extent than the webs It and terminate at their inner ends in axially-directed flanges I! so that the webs 15 have a T-section.
  • the webs l5, l6 and wall 14 will be at substantially the same temperature whereby thermal stresses due to the presence of external webs are avoided.
  • outward-facing surfaces [8 of th flanges I! are machined to be curved about the axis XX ( Figure 1) of the casing and the inwardly facing surfaces 19 of the webs 16 are machined to be similarly curved.
  • each blade has its axially spaced edges machined to provide inwardlyfacing surfaces 20 which are curved about the casing axis XX, the edges being recessed in the thickness of the platform so that the surfaces Zil are set back from the front face 2
  • the surface of the platform remote from the blade is formed intermediate the axially spaced edges with a rib 23 the outwardly facing surface 24 of which is machined to be curved about the casing axis XX.
  • the radial extent of the rib 23 is such that when the blade is assembled in a groove between the webs IS with the curved surfaces 20 in blade-retaining abutment with the surfaces ll, the surfaces 24 will cooperate with the surfaces [9 on the webs 16.
  • the curved surfaces 18, 24 will be clearly seen in the axial end view of the blade illustrated in Figure 5.
  • the blades 12 are mounted in the casing by sliding them around the grooves from the division between the parts 10, H with the surfaces 20 in engagement with the surfaces 18 and the surfaces 24 in engagement with the surfaces [9. It will be appreciated that the blades will thereby be retained accurately in position with the blade radial to the casing axis, whilst accuracy of machining is facilitated owing to the small area of the co-operating surfaces.
  • the platforms I3 of the blades 12 of each stage will abut through their circumferentially spaced edges so as to form a substantially continuous ring.
  • washers 25 ( Figures 2 and 4) which are accommodated in recesses 26 in the jointing flanges 21 formed on the parts, [9, II, and which engage the circumferentially-spaced edges of the platforms 13 of the end blades in the parts.
  • the washers 25 are held in position by bolts 28 which thread into bushes 29 secured in the casing parts.
  • the edges of the blades with which the washers engage are cut back as illustrated at 30 in Figure 5 to receive the Washers.
  • the parts ID, H are secured together by bolts 3
  • FIGs 6A, 6B, 60 are continuations one of the other in order, and illustrate the disposition of the end platforms of the stator blades in each of the 11 stages of the compressor. It will be appreciated that since the number of blades in each stage increases from the first stage of the compressor to the eleventh stage and since the diameter of the casing decreases, the chordal dimension of the platforms decreases from stage to stage.
  • the number of blades accommodated in say the part I0 is one greater than in the part H, so that the platforms l3l of the end blades in casing part 40 project at each stage by amount approximately equal to one quarter of the chordal dimension beyond the diametral line XX and the platforms I32 of the end blades in each stage of other part II are set back by approximately one quarter of the chordal dimension from the diametral line.
  • the joint between the parts H), II indicated in Figures 6A, 6B, 6C is therefore made to lie in a plane which is inclined to the diametral plane and which substantially contains the end surfaces of the end blades of each stage.
  • the line of division Y-Y between the parts 10 and If is thus displaced from the diametral line X--X at each stage by an amount substantially equal to the amount by which the blade platform I3I at that stage extends beyond the diametral line.
  • of stages 2, 3, 4, 5, 9, i0 and if he in the plane of division, that of the first stage lies slightly beyond the plane, and those of the remaining stages lie slightly below the plane of division.
  • the extent by which the end surfaces project or are set back from the plane of division can however be limited to a maximum of say $0.025 inch.
  • this invention provides a construction of stator-blade and stator-casing whereby manufacture and assembly of the compressor stator is simplified, and further that the compressor stator is of a strong but light construction and clean external appearance.
  • the blade platform may be provided as illustrated in Figure '7 in which the same references as previously used are employed to indicate corresponding parts, with a pair of outwardlydirected, axially-spaced, curved surfaces 24 intermediate the axially-spaced edges thereof, for example by being provided with a pair of radially extending ribs 23, to co-operate with corresponding inwardly-directed curved surfaces !9 formed internally of the wall M of the casing, for example by providing thereon a pair of webs such as 'webs 16 between each pair of webs l5.
  • An axial-flow compressor stator assembly comprising a stator casing having a relatively thin Wall, a plurality of axially-spaced main internal reinforcing webs each main web extending circumferentially around and project ing radially inwardly from the wall and each main web being formed with axially-spaced outwardly facing abutment surfaces curved about the axis of said casing, and a plurality of intermediate internal reinforcing webs there being at least one intermediate web between each pair of said main webs, each said intermediate web extending circumferentially around and projecting radially inwardly from said wall and being formed with an inwardly-facing abutment surface curved about the axis of said casing; and a plurality of stages of stator blading, each stage of stator blading comprising a plurality of blades in circumferential assembly supported and located by a pair of main Webs and at least one intermediate web, the blades being formed with axially and circumferentially extending blade root
  • An axial-flow compressor stator assembly tending circumferentially around and projecting radially inwardly from the Wall and each main web being formed with axially-spaced outwardlyfacing abutment surfaces curved about the axis of said casing and being formed additionally with inwardly-facing surfaces curved about the axis of the casing to constitute portions of the outer wall of the working fluid passage through the stator casing, and a plurality of intermediate internal reinforcing webs, there being at least one intermediate web between each pair of said main webs, each said intermediate web extending circumferentially around and projecting radially inwardly from said wall and being formed with inwardly-facing abutment surface curved about the axis of said casing; and a plurality of stages of stator bl-ading, each stage of stator blading comprising a plurality of blades supported and located in circumferential assembly by a pair of main webs and at least one intermediate web, the blades comprising axially and circumferentially
  • An axial-flow compressor stator assembly as claimed in claim 5 in which said blade root platforms are formed each on the side remote from the blade with a circumferentially and radially extending rib having an axial dimension less than the axial dimension of the blade root platform and having at its radially outer end the outwardly-facing abutment surface arranged to abut the inwardly-facing abutment surface of an intermediate web between said adjacent main Webs to maintain said main webs in contact with said blade root platform and thereby to locate the blade against radial and rocking movement.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US7488A 1947-02-17 1948-02-10 Stator for axial compressors Expired - Lifetime US2543355A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB270937X 1947-02-17

Publications (1)

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US2543355A true US2543355A (en) 1951-02-27

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US7488A Expired - Lifetime US2543355A (en) 1947-02-17 1948-02-10 Stator for axial compressors

Country Status (5)

Country Link
US (1) US2543355A (en, 2012)
BE (1) BE488535A (en, 2012)
CH (1) CH270937A (en, 2012)
FR (1) FR961133A (en, 2012)
GB (3) GB621544A (en, 2012)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2645413A (en) * 1947-04-16 1953-07-14 Rolls Royce Stator for multistage axial compressors
US2661147A (en) * 1949-01-19 1953-12-01 Ingersoll Rand Co Blower blade fastening device
US2749026A (en) * 1951-02-27 1956-06-05 United Aircraft Corp Stator construction for compressors
US2833463A (en) * 1953-11-06 1958-05-06 Rolls Royce Stator construction for axial flow compressor
US2848156A (en) * 1956-12-18 1958-08-19 Gen Electric Fixed stator vane assemblies
US2945290A (en) * 1957-09-16 1960-07-19 Gen Electric Stator vane half ring assemblies
US3262677A (en) * 1963-11-27 1966-07-26 Gen Electric Stator assembly
US3302926A (en) * 1965-12-06 1967-02-07 Gen Electric Segmented nozzle diaphragm for high temperature turbine
US3644057A (en) * 1970-09-21 1972-02-22 Gen Motors Corp Locking device

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB799896A (en) * 1955-10-21 1958-08-13 Rolls Royce Improvements in or relating to axial-flow compressors
US3070352A (en) * 1957-11-06 1962-12-25 Gen Motors Corp Vane ring assembly
NL8204723A (nl) * 1982-12-07 1984-07-02 Philips Nv Elektrische lamp.

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US735054A (en) * 1903-04-22 1903-08-04 Gen Electric Means for adjusting intermediate buckets.
US868419A (en) * 1905-05-18 1907-10-15 Gen Electric Turbine-bucket.
US990321A (en) * 1908-10-08 1911-04-25 George Westinghouse Turbine-blading.
US2220616A (en) * 1936-02-29 1940-11-05 Roder Karl Packing for steam turbines
US2240742A (en) * 1937-11-26 1941-05-06 Allis Chalmers Mfg Co Turbine blade attachment and method and apparatus therefor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US735054A (en) * 1903-04-22 1903-08-04 Gen Electric Means for adjusting intermediate buckets.
US868419A (en) * 1905-05-18 1907-10-15 Gen Electric Turbine-bucket.
US990321A (en) * 1908-10-08 1911-04-25 George Westinghouse Turbine-blading.
US2220616A (en) * 1936-02-29 1940-11-05 Roder Karl Packing for steam turbines
US2240742A (en) * 1937-11-26 1941-05-06 Allis Chalmers Mfg Co Turbine blade attachment and method and apparatus therefor

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2645413A (en) * 1947-04-16 1953-07-14 Rolls Royce Stator for multistage axial compressors
US2661147A (en) * 1949-01-19 1953-12-01 Ingersoll Rand Co Blower blade fastening device
US2749026A (en) * 1951-02-27 1956-06-05 United Aircraft Corp Stator construction for compressors
US2833463A (en) * 1953-11-06 1958-05-06 Rolls Royce Stator construction for axial flow compressor
US2848156A (en) * 1956-12-18 1958-08-19 Gen Electric Fixed stator vane assemblies
US2945290A (en) * 1957-09-16 1960-07-19 Gen Electric Stator vane half ring assemblies
US3262677A (en) * 1963-11-27 1966-07-26 Gen Electric Stator assembly
US3302926A (en) * 1965-12-06 1967-02-07 Gen Electric Segmented nozzle diaphragm for high temperature turbine
US3644057A (en) * 1970-09-21 1972-02-22 Gen Motors Corp Locking device

Also Published As

Publication number Publication date
GB621544A (en) 1949-04-11
GB621547A (en) 1949-04-11
BE488535A (en, 2012)
FR961133A (en, 2012) 1950-05-05
GB621551A (en) 1949-04-11
CH270937A (de) 1950-09-30

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