US3905722A - Fluid flow machines - Google Patents

Fluid flow machines Download PDF

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Publication number
US3905722A
US3905722A US340118A US34011873A US3905722A US 3905722 A US3905722 A US 3905722A US 340118 A US340118 A US 340118A US 34011873 A US34011873 A US 34011873A US 3905722 A US3905722 A US 3905722A
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US
United States
Prior art keywords
blade
platform
blades
rotor
fluid flow
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
US340118A
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English (en)
Inventor
Kenneth Ronald Guy
Harry Dennis
Robert Burns Hood
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
Original Assignee
Rolls Royce 1971 Ltd
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 Rolls Royce 1971 Ltd filed Critical Rolls Royce 1971 Ltd
Application granted granted Critical
Publication of US3905722A publication Critical patent/US3905722A/en
Anticipated expiration legal-status Critical
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Classifications

    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/50—Vibration damping features

Definitions

  • a fluid flow machine has a plurality of compressor blades, each blade has aerofoil and root portions together with a platform portion which is made of a material of a difi'erent nature to that of the blade, and which is joined to it.
  • the blade is titanium and the platform portion is a foamed polyurethane resin.
  • Such blades generally comprise aerofoil, platform, and root portions and would typically be formed by forging operations to produce the general shape, followed by machining operations to produce the finished blade.
  • the platform assists the fluid flow through the machine and may, by contacting the platforms of adjacent blades in the fluid flow machine, provide a frictional clamping mechanism for blade vibrations.
  • a platform for a blade creates many manufacturing problems; in particular, for a forged blade the shape of the forging discs becomes more complicated and costly and the finished machining of the blade requires several operations to profile the platform.
  • compressor blades will be understood to include constructions such as ducted fan blades.
  • a compressor blade for use in a fluid flow machine, the blade having aerofoil and root portions together with a platform portion which is made of a material of a different nature to that of the blade and joined to the blade.
  • a method of manufacturing a compressor blade for use in a fluid flow machine comprises the steps of making a component having aerofoil and root portions and subsequently joining a platform portion to the blade, the platform portion being made of a material of a different nature to the blade.
  • a plurality of said compressor blades is arranged in an annular array and adjacent surfaces of adjacent platform portions are provided with anti-fretting coatings.
  • annular array comprises a number of segments and the platform portions of each blade within the segment is joined to the adjacent platform portions of adjacent blades within the segment.
  • An annular array of blades may be secured to a disc to form a bladed rotor or may be secured to a casing to form a stator row.
  • the platform portions of compressor blades comprising successive rotor or stator rows may be joined togethcr.
  • Leakage of the working fluid of a fluid flow machine between successive rotor and stator rows may be reduced by forming the platform portions to include sealing means.
  • One particular method of manufacturing a said compressor blade comprises the steps of making a compo nent having aerofoil and root portions, placing the component into a moulding box, and casting the platform portion onto the component.
  • a preferred material for the platform portion is a foamed polyurethane resin.
  • the moulding box is an exact female replica of the platform portion thus obviating the need for machining the as cast platform portion.
  • FIG. 1 shows a plan view of a blade according to the invention.
  • FIG. 2 is a view in the direction I of FIG. 1.
  • FIG. 3 is a segment of a bladed rotor provided with the blade of FIG. 1.
  • FIG. 4 is another segment of a bladed rotor showing an alternative embodiment.
  • FIG. 5 illustrates a blade in a moulding box for the purpose of casting the platform portion onto the blade.
  • FIG. 6 is a longitudinal section through part of a compressor showing a seal between compressor rotor row and a stator row.
  • FIG. 7 is a longitudinal section through part of a com' pressor showing the platform portions of two rotor rows joined together.
  • a compressor blade 10 has integral aerofoil, and root portions 1] and 13 respectively.
  • a bladed rotor 20 comprises a plurality of such blades 10 regularly spaced about, and extending in a radial direction from, the periphery 21 of the rotor disc 22 in an annular array 26 (only part of which is shown).
  • the blades I0 are secured to the disc by serrations 23 in its periphery which accommodate the root portions 13 ofthe blades.
  • a lug l5 and a locking device 16 prevent the blade moving axially relative to the disc 22.
  • the aerofoil portion 11 of the blade is blended di rectly into the root portion 13 without an integral platform.
  • the stresses in the blade may be led directly into the root avoiding the stress concentrations and other disadvantages that can be associated with forming a blade platform integrally with the blade, particularly the folds and cracks that can occur as a result of the severe deformation necessary to provide an integral platform on a forged blade are avoided, and the manufacturing process is simplified.
  • Each blade 10 is however fitted with a platform portion 24 the platform portion 24 being made in a material of different nature to the material of the blade.
  • the material is either a different material to that of the blade or is the same material but the material is of a different structure.
  • the blade may be of forged titanium and the platform portion may be of a titanium honeycomb or sintered from titanium powder the honeycomb or sintered structure being subsequently brazed to the aerofoil portion II of the blade 10.
  • the present embodiment involves the joining of a platform portion 24 in foamed polyurethane resin to a blade of forged titanium.
  • FIG. 5 will show a component 12, having aerofoil and root portions, partially enclosed in a moulding box 40.
  • the portion 39 of the component inside the moulding box has prior to inserting therein been cleaned and vapour blasted, and the inside of the moulding box coated with a releasing agent.
  • a valve 41 in the moulding box allows the admission of a known quantity of a polyurethane resin and a foaming agent.
  • the polyurethane resin and the foaming agent react to produce a foamed polyurethane resin which expands to fill the moulding box.
  • Air entrapped in the moulding box is allowed to escape through a venting valve 43.
  • the quantity of polyurethane resin and foaming agent added is in excess of the amount necessary to fill the moulding box 40 this results in a precompressed foamed resin which has improved mechanical properties.
  • the foamed polyurethane resin will quickly cure and this may be accelerated by warming the moulding box or by the addition of additives to the polyurethaneresin.
  • the moulding box is illustrated for use with a single component 12 but it will be readily appreciated that the technique can be extended to form platform portions 24 for a complete annular array of blades, adjacent platform portions 24 of adjacent blades being joined together to form an annular ring, or for a plurality of blades joined together in a segment as illustrated by the three blades of FIG. 4.
  • the annular ring may be formed about the blades when they are inserted in the disc or alternatively the blades may be located in a jig not shown during the moulding process and the whole assembly subsequently fitted to the rotor disc.
  • the moulding box 40 is an exact female replica of the shape of the platform portion 24 it is desired to produce thus obviating the need for any machining of the as cast platform.
  • the radially outer surfaces 25 of successive platform portions 24 are profiled to define, together with the radially inner wall 27 of a casing 28, in which the bladed rotor operates, a duct 29 suitable for efficient compression of the working fluid.
  • lf individual blades are provided with separate platform portions the end faces 30 of adjacent platform portions may be treated with antifretting compounds applied for example by plasma or metal spraying techniques.
  • foamed resin platform portion which has a low density in comparison with a metal may allow despite the greater volume necessary to ensure mechanical integrity, a weight saving. It is readily seen from FIG. 2 that the foamed resin extends for some distance along the aerofoil portion 1 l of the blade this ensures a good shear strength for the platform portion at its junction with the aerofoil portion ll and prevents centrifugal force from detaching it.
  • annular ring 44 or the platform portions 24 of the compressor blades are machined or cast to include seal elements 45 to reduce the leakage of working fluid between successive rotor or stator rows 46, 47 respectively of the compressor 48.
  • the sea] elements attached to the rotor row 46 can be seen facing seal elements 49 attached to the stator row 47.
  • the blades 50 of the stator row are also shown having platform portions 29, formed in foamed polyurethane resin.
  • FIG. 7 the platform portions of two successive rotor rows 46 are shown joined together. and the radially inner ends 51 of the blades 50 of the stator row face the joined together platform portions for sealing purposes.
  • a variety of different materials may be chosen for the platform portions of the blades of fluid flow machines constructed according to the invention. It will be appreciated that such materials should be chosen having regard to their working enviroment in particular the materials strength at the necessary operating temperature. its resistance to abrasion, its weight, its mechanical integrity and the strength of the joint with the aerofoil portion of the blade need to be considered.
  • a particular advantage of foamed polyurethane resin lies in the fact that little damage will be caused to the fluid flow machine should it become detached from the blade.
  • One type of foamed polyurethane resin used successfully by the applicants is Nopcofoam. (Registered Trade Mark).
  • the present temperature limit for foamed polyurethane resins is of the order of C above this temperature their mechanical properties are degraded to the point of being unacceptable. It is expected however that developments in the high temperature technology of resin systems in general will allow the extension of the technique to compressor blades operating at temperatures in excess of 120C.
  • Foamed polyurethane resin is a relatively flexible material in contrast to some resins which are relatively rigid. Differential thermal expansion between a blade and the platform portion can lead to cracking of the platform portion from the blade if the platform portion is made of a relatively rigid material. This cracking can be avoided by interposing a layer of relatively flexible material between the blade and the platform portion. A layer of a nitrile phenolic of approximately fifty to sixty thousandths of an inch has been found successful for this purpose.
  • a rotor for a fluid flow machine comprising a rotor body; an annular array of blades connected to and extending radially from said body, each blade having an aerofoil portion whose radially inner end terminates in a position spaced from the periphery of the body and a shank extending between the aerofoil portion and said periphery; and platform means made of a cellular material arranged between adjacent shanks.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US340118A 1972-03-15 1973-03-12 Fluid flow machines Expired - Lifetime US3905722A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1195472A GB1428365A (en) 1972-03-15 1972-03-15 Fluid flow machines

Publications (1)

Publication Number Publication Date
US3905722A true US3905722A (en) 1975-09-16

Family

ID=9995693

Family Applications (1)

Application Number Title Priority Date Filing Date
US340118A Expired - Lifetime US3905722A (en) 1972-03-15 1973-03-12 Fluid flow machines

Country Status (6)

Country Link
US (1) US3905722A (it)
JP (1) JPS5430124B2 (it)
DE (1) DE2312631A1 (it)
FR (1) FR2176433A5 (it)
GB (1) GB1428365A (it)
IT (1) IT979842B (it)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4019832A (en) * 1976-02-27 1977-04-26 General Electric Company Platform for a turbomachinery blade
US4045149A (en) * 1976-02-03 1977-08-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Platform for a swing root turbomachinery blade
US4175912A (en) * 1976-10-19 1979-11-27 Rolls-Royce Limited Axial flow gas turbine engine compressor
US4177013A (en) * 1977-01-11 1979-12-04 Rolls-Royce Limited Compressor rotor stage
US4265594A (en) * 1978-03-02 1981-05-05 Bbc Brown Boveri & Company Limited Turbine blade having heat localization segments
US4326836A (en) * 1979-12-13 1982-04-27 United Technologies Corporation Shroud for a rotor blade
US4494909A (en) * 1981-12-03 1985-01-22 S.N.E.C.M.A. Damping device for turbojet engine fan blades
US4655687A (en) * 1985-02-20 1987-04-07 Rolls-Royce Rotors for gas turbine engines
US4850802A (en) * 1983-04-21 1989-07-25 Allied-Signal Inc. Composite compressor wheel for turbochargers
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
US20050028839A1 (en) * 2003-08-07 2005-02-10 Macquoid Malcolm Method for cleaning fluid spills using biodegradable absorbent material and for transporting the same
US8827651B2 (en) 2010-11-01 2014-09-09 Rolls-Royce Plc Annulus filler

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9300579D0 (en) * 1993-01-13 1993-03-03 Esselte Dymo Nv Tape cutting apparatus
EP2884052B1 (de) * 2013-12-13 2018-02-21 Siemens Aktiengesellschaft Rotor für eine strömungsmaschine mit geschlossenem strömungskonturring und verfahren zur herstellung desselben
FR3120389B1 (fr) * 2021-03-04 2023-06-02 Safran Aircraft Engines Ensemble pour un rotor pour une turbomachine

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2858103A (en) * 1956-03-26 1958-10-28 Westinghouse Electric Corp Gas turbine apparatus
US3294366A (en) * 1965-04-20 1966-12-27 Rolls Royce Blades for gas turbine engines
US3494539A (en) * 1967-04-03 1970-02-10 Rolls Royce Fluid flow machine
US3515501A (en) * 1967-04-12 1970-06-02 Rolls Royce Rotor blade assembly
US3549444A (en) * 1967-12-28 1970-12-22 Harry S Katz Filament wound blade and compressor
US3719431A (en) * 1969-09-26 1973-03-06 Rolls Royce Blades

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2858103A (en) * 1956-03-26 1958-10-28 Westinghouse Electric Corp Gas turbine apparatus
US3294366A (en) * 1965-04-20 1966-12-27 Rolls Royce Blades for gas turbine engines
US3494539A (en) * 1967-04-03 1970-02-10 Rolls Royce Fluid flow machine
US3515501A (en) * 1967-04-12 1970-06-02 Rolls Royce Rotor blade assembly
US3549444A (en) * 1967-12-28 1970-12-22 Harry S Katz Filament wound blade and compressor
US3719431A (en) * 1969-09-26 1973-03-06 Rolls Royce Blades

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4045149A (en) * 1976-02-03 1977-08-30 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Platform for a swing root turbomachinery blade
US4019832A (en) * 1976-02-27 1977-04-26 General Electric Company Platform for a turbomachinery blade
US4175912A (en) * 1976-10-19 1979-11-27 Rolls-Royce Limited Axial flow gas turbine engine compressor
US4177013A (en) * 1977-01-11 1979-12-04 Rolls-Royce Limited Compressor rotor stage
US4265594A (en) * 1978-03-02 1981-05-05 Bbc Brown Boveri & Company Limited Turbine blade having heat localization segments
US4326836A (en) * 1979-12-13 1982-04-27 United Technologies Corporation Shroud for a rotor blade
US4494909A (en) * 1981-12-03 1985-01-22 S.N.E.C.M.A. Damping device for turbojet engine fan blades
US4850802A (en) * 1983-04-21 1989-07-25 Allied-Signal Inc. Composite compressor wheel for turbochargers
US4655687A (en) * 1985-02-20 1987-04-07 Rolls-Royce Rotors for gas turbine engines
US5277548A (en) * 1991-12-31 1994-01-11 United Technologies Corporation Non-integral rotor blade platform
US20050028839A1 (en) * 2003-08-07 2005-02-10 Macquoid Malcolm Method for cleaning fluid spills using biodegradable absorbent material and for transporting the same
US8827651B2 (en) 2010-11-01 2014-09-09 Rolls-Royce Plc Annulus filler

Also Published As

Publication number Publication date
JPS48102306A (it) 1973-12-22
DE2312631A1 (de) 1973-09-20
JPS5430124B2 (it) 1979-09-28
FR2176433A5 (it) 1973-10-26
IT979842B (it) 1974-09-30
GB1428365A (en) 1976-03-17

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