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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EP 0 416 186 A3

(12)	EUROPEAN PATENT APPLICATION

(88)	Date of publication A3:
	24.07.1991 Bulletin 1991/30

(43)	Date of publication A2:
	13.03.1991 Bulletin 1991/11

(21)	Application number: 89312535.1

(22)	Date of filing: 30.11.1989

(51)	International Patent Classification (IPC)⁵: F04D 29/32

(84)	Designated Contracting States:
	AT BE CH DE ES FR GB GR IT LI LU NL SE

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Priority:

08.09.1989 GB 8920415

(71)	Applicants:
	Eggleton, Frederick Nelson Lancashire BB9 7LZ (GB) Fenwick, Constance Clare West Yorkshire, LS2I IJZ (GB) Trafford, Judith Caroline Scarboruogh North Yorkshire, YOI3 9HU (GB)

(72)	Inventors:
	Eggleton, Frederick Nelson Lancashire BB9 7LZ (GB) Fenwick, Constance Clare West Yorkshire, LS2I IJZ (GB) Trafford, Judith Caroline Scarboruogh North Yorkshire, YOI3 9HU (GB)

(74)	Representative: Denmark, James
	Bailey, Walsh & Co. 5 York Place Leeds LS1 2SD Yorkshire Leeds LS1 2SD Yorkshire (GB)

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References cited: :


	Remarks:
	A request for correction pages 9, 15 and 21 has been filed pursuant to Rule 88 EPC. A decision on the request will be taken during the proceedings before the Examining Division (Guidelines for Examination in the EPO, A-V, 2.2).

(54)	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)

(57) An AXIAL FLOW AIR COMPRESSOR DESIGN SYSTEM to produce a compressor in which AIR SPRING ENERGY DESIGNATED Esp(1.2). which is generated between PLANES 1. & 2. is fully used between PLANES 2. & 3. The the blade arc width being such that the blades give full static coverage to its OUTLET PLANE 4. The lamina air flow through each FULL STAGE being as follows:-

PLANE 1.- W(1.3). + (va1². + vcm1².)/2.g. + y.p1.v1./(y-1.). =

PLANE 2.- W(2.3). + (va2²).+ vcm1².)/2.g.+ y.p2.v2./(y-1.). + Esp(1.2). =

Plane 3.- (va3².+ vcml².)/2.g. + y.p2.v2./(y-1.).

PLANE ₄.- (_va3².+ vcm1².)/2.g. + y.p2.v2./(y-1.). - End of Rotor. Start of STATORS.

PLANE 5.- y.p2.v2./(y-1.). + (va3².+ vcm1².)/2.g.

PLANE 6.- y.p2.v2./(y-1.). + (va6². + vcm6².)/2.g.

PLANE 7.- ALL VALUES EXACTLY AS ON PLANE 6.

PLANE 8.- y.p8.v8./(y-1.). + (va8². + vcm8².)/2.g.

NOTE:- p. = Air pressure EXCLUSIVE of that due to the presence of Esp(1.2) at PLANE 2.

WHILE NOT BEING STIPULATED, the Mean Mass Flow Values have been arranged such that sets of lamina values become also Mean Mass Flow Values, for EXAMPLE Esp(1.2)_r=x/2. = m Esp(1.2)_r=x. & va2_r=_x/2. = m va2_r=x. etc.

Also:- Va8_r=Max.No./2· and vcm8_r=Max.No./2. = va1_r=Max.No./2. and vcm1_r=Max.No./2. and are constant values for all stages of a compressor.

And (va6_r./vcm6_r.) = (va7_r./vcm7_r.) = (va8_r./vcm_8r.).

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