EP0416186A2 - Rotorschaufeln eines Axialverdichters besonders gebildet zur Behaltung der Existenz der mit Esp. angedeuteter Energie innerhalb ihren axialen Arbeitslänge bestimmt mit der Dimension L (I.3) - Google Patents

Rotorschaufeln eines Axialverdichters besonders gebildet zur Behaltung der Existenz der mit Esp. angedeuteter Energie innerhalb ihren axialen Arbeitslänge bestimmt mit der Dimension L (I.3) Download PDF

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Publication number
EP0416186A2
EP0416186A2 EP89312535A EP89312535A EP0416186A2 EP 0416186 A2 EP0416186 A2 EP 0416186A2 EP 89312535 A EP89312535 A EP 89312535A EP 89312535 A EP89312535 A EP 89312535A EP 0416186 A2 EP0416186 A2 EP 0416186A2
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EP
European Patent Office
Prior art keywords
ref
plane
vcm1
esp
blade
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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.)
Withdrawn
Application number
EP89312535A
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English (en)
French (fr)
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EP0416186A3 (en
Inventor
Frederick Eggleton
Constance Clare Fenwick
Judith Caroline Trafford
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Individual
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Individual
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Publication date
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Publication of EP0416186A2 publication Critical patent/EP0416186A2/de
Publication of EP0416186A3 publication Critical patent/EP0416186A3/en
Withdrawn legal-status Critical Current

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    • 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors

Definitions

  • Multi stage axial flow compressors are used to effect the compression of large air mass flows to high pressures.
  • Each individual stage comprising of a ring of rotor blades followed with running clearance between by a ring of stator blades.
  • the rotor blade ring is required to add kinetic energy alone or kinetic and heat energy to the air while the stator ring of blades change the surplus whirl velocity kinetic energy into heat energy.
  • the blade shape and speed of rotation being arranged also to maintain a constant value axial air velocity along all streamlines but not necessarily all of the same value.
  • a specific embodiment of the invention is thus rotor blade rings, each blade of which has a precisely calculated shape such that the energy Esp-(1.2). generated in the air through the first portion of the blade ring is constructively used to help drive the second portion thus eliminating itself from the air flow.
  • the Bernoulli type equation which identifies the various forms of energy involved in the action between the inlet plane (Plane 1.) and the plane which terminates the working length of the blade (Plane 3.) is qiven below:-
  • W(1.3). The energy per unit air mass flow required to drive the Plane 1. to 3. portion of the rotor blade ring.
  • the inlet and outlet plane outer edges are both equal in radius and angular extent. That at the outlet plane due to the air whirl velocity being angularly ahead in the direction as of the rotation of the blades, of the inlet plane.
  • the inside edges are both arcs, that of the outlet plane being angularly ahead for the same reason as the outer arc. Both arcs are equal in angular extent but the arc at the outlet plane is at a larger radius than that at the inlet plane.
  • the inside arcs can be at an equal, greater, or lesser axial distance apart than the outer arcs.
  • the axial projection of both end planes are sectors of their respective annulus.
  • the outer boundary surface that joins the two above planes together is of constant arc radius but not of angular extent, the latter being of minimum extent at Plane 2.
  • the surface also spiralling at a varying rate from inlet to outlet plane.
  • the inner boundary surface joining the two inner arcs is of a constant arc radius from Plane 1. to Plane 2., (optionally to Plane 3.). Plane 2. being position of minimum angular extent. From Plane 2. to Plane 4. (Outlet plane) both angular extent and arc radius increase at rates which are related to each other to maintain from Plane 2. a constant cross sectional area airstream to the outlet plane. Additional to the foregoing and similarly to the outer surface it spirals in the same direction.
  • the airstream is divided by intermediate streamlines into lasser portions of the full air mass flow.
  • the radial depth on Plane 1. is divided into an even number of equal portions.
  • the air mass flowing between the common outer boundary and any one of the others is calculated for Plane 1. and is retained by the streamline to the outlet plane.
  • Ep(1.2). ((v1./v2.) (y-1.) .- 1.).T1.C./(y-1.).
  • vr2. Specific Volume of the air mass in the rear portion of the cylinder (Adjacent to piston).
  • V1R. has the minimum velocity
  • vb1 R . should have a value not exceeding (V1 R . + va1 R .).
  • the rotor blade shape (As manufactured) when stationary is also its absolute shape.
  • V1. the rotor blade absolute shape continuously in contact with its relative shape on Plane 1. appears to move in an anti-clockwise direction like a pointer of a clock until at the designed speed it reaches the designed speed position.
  • the absolute shape passes through a third position where it is disposed axially. This is the position where surge conditions would arise if the relative blade shapes did not give full static coverage to the inlet plane.
  • the rotor blade at all radii should have a minimum arc length of one blade pitch.. (See Figure 9/9.)
  • the absolute lamina blade circular arc dimensions are measured from an axial line which passes through the blade point at Plane 1. and the axial length dimensions from Plane 1. along the line. Note also that all streamlines in the Synopsis are at a constant radius thus r(1.3).
  • Front profile dimension designations are prefixed by the letters Fp and rear profile dimensions Rp.
  • the mean centre line of air mass flow moved circumferentially one half blade pitch so that it can be dimensioned from the above axial line uses the prefix S.
  • the blade length is divided into three sections a., b., c. which represent (Plane 1. to 2.)., (Plane 2. to 3.) and (Plane 3. to 4.) and thus:-
  • Synopsis is not compiled for any specific air mass flow but to provide relationships between the dimensions of the air duct and rotor blades to the large number of different air and blade velocities and air conditions which simplify the design of a compressor having a specific air mass flow.
  • the first requirement is the choice of the following values:-V1 0 ., r(1.3)o., r(1.3) r ., No. of blades in ring., Ratios (P2 r ./Z2 r .)., ICAC Standard Atmosphere air conditions., a stipulation of the value of va1 R ., a stipulation of the value of the Ratio (vcm1 R ./Max.vcm1 R .) From which are derived all other values on either Synopsis 1A. or 1D. (1D. used in example):-
  • Root Streamline Column applicable to Synopsis 1A. or 1D.
  • Ref.No. 9 .- C3 R . (1. + ((B.- A.)/B.) 1/2 .)
  • A. ((P2 R ./Z2 R .) (y-1.) .- 1.)
  • B. (((P2 R ./(2.Z2 R .- P2 R .)) (y-1.) .- 1.)/2.)
  • (P2 R ./(2.Z2.- P2 R .)) (1./2.Z2 R ./P2 R .- 1.))
  • Ref.No.12. - Ba1 0 . b 0 .+ Ei(1.2) 0 .2.g./vb1 0 2 .
  • Ref.No.13. - va1 0 . V1 0 .- V1 R .)/2. + va1 0 .
  • vb2o. (E(1.2) 0 .2.g./(1. + 1/b 0 .)) 1/2 . + va1o.
  • Ref.No.19. - va3 0 . C3 0 .(va2 0 .- va1 0 .) + va1 0 .
  • Ref.No.20. - vb1 0 . ((va2 0 .- va1 0 .)/b 0 .) + va2 0 .
  • Ref.No.21. - vb3o. vb1 0 .- (va3o.- va1o.)/bo.
  • Ref.No.79 .- L(1.w) r . L(1.3) r .+ + w.L(3.4) r ./W.
  • Ref.No.79A .- L(3.4) r . L(1.4) r .- L(1.3) r .
  • Ref.No.79B .- L(1.4) r . vcm1 r .t(1.4) r .
  • Ref.No.79C .- t(1.4) r . (P1 r .- t(1.3) r .(va3 r .- m va-(1.3)r.))/(V1r.- va3 r .).
  • Ref.No.83 .- rw r . b./2.a. + ((b./2.a.) 2 . + c./a.)- 1/2 .
  • Ref.No.80 .- Fpcw r . Fpb3 r .+ w.t(3.4) r .va3 r ./W. - (X3 r .- Xw r .)/2.
  • Ref.No.81 .- Scw r . Sb3 r . + w.t(3.4) r .va3 r ./W.
  • Ref.No.82 .- Rpcw r . Rpb3 r . + w.t(3.4) r .va3 r ./W. + (X3 r .- Xw r .)/2.
  • Ref.No.41 .- Ar1 r . Pi.(r(1.3) 0 . - r(1.3) r 2 .).
  • Ref.No. 1 .- r(1.3) R . (r(1.3) 0 2 .- Stage 1.Ar 8 R./Pi.) 1/2 .
  • Ref.No. 1 .- r(1.3),. r(1.3) o . - (Str.No.)(r(1.3) o . -r(1.3) R .)/(Max.Str.No.).
  • Ref.No.5 .- V1,. r(1.3) r .V1o./r(1.3)o.
  • Ref.No.43 .- M1 r . Ar1 r .m vcm1 r ./m v1 r . Ref.Nos. 9.,10.,30.,31.,32.,33.,35.,38.,39., & 40. - C3 r .,C4 r ., E(1.2) r ., Ep(1.2) r ., Ei(1.2) r ., Esp(1.2) r ., W(i.2) r ., T2 r ., p2 r ., v2 r ., Formulae for their derivation are as used for Stage 1. Synopsis.
  • Ref.No.14 .- vcm1 r . (1.x 14.) r ./r(1.3) r .
  • Ref.No.13 .- va1 r . (Stage 1.(va1 r 2 . + vcm1 r 2 .) -vcm1 r 2 .) 1/2 .
  • the axial length of the stators is divided into two parts by a short length interposed for the adjustment of total length for mechanical reasons.
  • the basic planes being as follows:-Inlet Plane 5.
  • This plane except for being divided by a different number of blades is exactly as the preceding rotor outlet plane.
  • Air conditions at these two planes are exactly alike. Except for allowing for the rotation of the air, dimensions are also alike.
  • the function of the first portion of the blades is to move the streamlines radial position so that at Plane 6. they are axially in line with their position on Plane 8.
  • a second requirement is to change the proportions of va5 and vcm5. such that the ratios va6 r ./vcm6 r ., va7 r ./vcm7 r . and va8 r ./vcm8 r . are of the same value.
  • the function of the rear portion of the blades is to reduce the air velocities va7 r ./vcm r . via van r ./vcmn r . to va8 r ./vcm8 r . while changing the surplus of kinetic energy into heat energy. by diffusion.
  • Ref.No.60 .- M8 r . As Stage 1. Rotor Plane 1. Ref.No.43. - m Q8 r .
  • Ref.No.39 L(5.6) r X6 r /(((vcm6,: vcm5 r .)-t(va5,.- va6 r .)) -(va8 r ./vcm8 r .)).
  • Ref.No.39 .- L(5.6) r . Rp r .(Sin.Q5 r .- Sin.Q6 r .).
  • Ref.No.30.-t(6.7) r . L(6.7) r ./vcm6,.
  • Ref.No.39 .- L(5.7) r . L(5.6) r . + L(6.7) r .
  • Ref.No.38 .- t(5.7) r . t(5.6) r . + t(6.7) r .
  • Ref.No.53 .- SFp6 r . Tan.Q6 r .L(5.6) r .
  • Ref.No.53 .- SFp7 r . Tan.Q6 r .L(5.7) r .
  • Ref.No.54 SRp7 r SFp7 r . + X6 r .
  • X6 r . Z7r.
  • Ref.No.54 .- SRp6 r . SFp6 r . + X6 r .
  • the second method which was applied to the example is to use the values m Qm r ., Qm r ., and Xm r . as before and arrange a curve of constant arc radius whose radius centre would lie on a radial line intercepting Plane 6. of the inner streamline, and in a similar way for the other streamlines.
  • the latter curves are thus the mean of the calculated ones.
  • the effect of of the latter when the area Arxm r . is greater is to slow down the value of m Rvxm r . to m Rvm r . and if less to speed up the value m Rvxm r . to the value of m Rvm r .
  • m vcmxm r is to use the values m Qm r ., Qm r ., and Xm r .
  • Rvxm r . Rvm r .m Rvxm R ./m Rvm R .
  • - rm r . (Rx r 2 .- (L(5.6) r .- L(5.m) r .) 2 .)- 1/2 +(r6 r .- Rx r .).
  • Rx r . (L(5.6) r 2 ./2.(r6 r .- r5 r .).). + (r6 r .- r5 r .)/2.
  • Ref.No.39. - L(5.m) r . (Rp r .(va5 r .- vam r .))IRvS r .
  • Rp r . (L(5.6) r 2 ./2.(r6 r .- r5 r .).). + (r6 r .- r5 r .)/2.
  • Um r . ((Pi./2)- Qm r .). and U5 r . ((Pi./2)-Q5r.)
  • Qm r . and Q5 r . are in Radians.
  • Ref.No.38. - t(5.m) r . L(5.m) r ./m vcm(5.m) r ).
  • - SFpm r . Sin.Q6 r .L(5.m) r .
  • - SRpm r . SFpm r . + Xm r .
  • Ref.No.58. - Rvn r . Rv7 r . - n.(Rv7 r .- Rv8 r .)/N.
  • Ref.No.58 .- m Rvn r . m Rv7 r . - n.(m Rv7 r .- m Rv8 r )/N.
  • Ref.No. 1 .- m van r . m va7 r .- n.(m va7 r .- m va8 r .)/N.
  • m van r Sin.m Q8 r .m Rvn r . Ref.No.
  • v7 r .(T7 r ./Tn r .) 1/(y-1) . Ref.No. 4 .- m pn r . m p7 r .(m Tn r ./m T7 r .) y(y-1)-

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Pharmaceuticals Containing Other Organic And Inorganic Compounds (AREA)
  • Acyclic And Carbocyclic Compounds In Medicinal Compositions (AREA)
EP19890312535 1989-09-08 1989-11-30 Axial compressor rotor blades specifically shaped to confine the existence of the energy designated esp. to within their axial working length defined by the dimension l (i.3) Withdrawn EP0416186A3 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB8920415A GB2250322A (en) 1989-09-08 1989-09-08 Axial flow air compressor blade
GB8920415 1989-09-08

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EP0416186A2 true EP0416186A2 (de) 1991-03-13
EP0416186A3 EP0416186A3 (en) 1991-07-24

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EP19890312535 Withdrawn EP0416186A3 (en) 1989-09-08 1989-11-30 Axial compressor rotor blades specifically shaped to confine the existence of the energy designated esp. to within their axial working length defined by the dimension l (i.3)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6773187B2 (en) 2000-10-03 2004-08-10 L'oreal S.A. Device and method for packaging and applying a substance
US6945723B1 (en) 2000-09-21 2005-09-20 L'oréal Packaging and application device

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB741797A (en) * 1953-12-21 1955-12-14 Sulzer Ag Rotors for centrifugal pumps, blowers and compressors
GB944166A (en) * 1960-03-02 1963-12-11 Werner Hausammann Rotor for turbines or compressors
GB1599633A (en) * 1978-04-17 1981-10-07 Hodgson D I Aerofoils
CA1205709A (en) * 1981-08-31 1986-06-10 Elias H. Razinsky Airfoil for high efficiency/high lift fan

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
No further relevant documents have been disclosed. *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6945723B1 (en) 2000-09-21 2005-09-20 L'oréal Packaging and application device
US6773187B2 (en) 2000-10-03 2004-08-10 L'oreal S.A. Device and method for packaging and applying a substance
US7156572B2 (en) 2000-10-03 2007-01-02 L'oreal S.A. Device and method for packaging and applying a substance

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EP0416186A3 (en) 1991-07-24
GB8920415D0 (en) 1989-10-25
GB2250322A (en) 1992-06-03

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