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AIR DOCUMENTS DIVISION

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HEADQUARTERS AIR MATERIEL COMMAND

WRIGHT FIELD, DAYTON, OHIO

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ATI No.' 66^ NAIiONALGASTURBlNI

ESTABLISHMENT

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J _ rforuance ju-f;. i'or three axial flow ooimru^ora with low. m< -i .1:1 j r.: '•..' h__._ .•,,;•:• ': _;_ .

356823

.:- ""varcino Establishment,

.me, Lelc Wh ".roh, 19A-7.

Inctoture / to Report N* /.t...»A~~i Miliury Aiuihe, London.

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Eggt Jet» MaggSäB 8S» &LUB3

OaloDilated performance curves for three axial flow MBDWMOT •gth low, uedlum Mid hioh stamier blades

-by -

Märiorie »SSSHh

Stft Pin/1301-AX)A»/IB. April, 1%6.

Hl1 ITI

In the absence of complete test characteristics for axial compressors frith low, medium and high stagger bladings, estimates of performance have been mu.de for three typical compressors, t-nl the results obtained are given in this memorandum. Though the results axe only strictly applicable; to the compressors that were designed, they probably show the changes that may be generally expected between compressor blades of various stagers. The slope of the pressure ratio curves became steeper and the value of the et'fioiency falls more rapidly away from the design speed with on increase in stagger. The maximum efficiency, however, is further away from the surge point at the higher staggers.

1.0 Introduction

In the past, in this country, compressors hwre been mostly designed with lov stagger blades, -hile in Africa und on the Continent» high stagger blades have generally been used, A fair amount of test data is available here on low stagger blading, but as yet no corresponding complete characteristics were available on blading with high stagger. So that, this theoretical investigation was carried out in order to provide typical but comparable performance curves for low, medium and high stagger compressors.

To make the results directly comparable, all the compressors have the same overall temperature r.se at the design point and the saute mass flow.

A diffuser loss of total head has been assumed in the calculations, so that pressure ratios and efficiencies may be taken to be those at entrance to the combustion chamber*.

2,0 The design of the compressors.

Each compressor has been designed to have a mass flow of 50 lbs/sec. and a temperature rise of 166°C in eight stages. This gives a pressure ratio in each case of slightly over if i 1,

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B.J.JL 1201

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The design air outlet angles (ag") for the biades of the low, medium and high stagger compressors were chosen to bo 15°« 50° «ad 45° respectively at mean diameter. Theae gave ataggera of -20.6°, -54.2° and-47.5° at mean diameter. and have parabolic arc caabers.

The blades are conatant reaction

The design r.p.ra. (N) for tne low, medium and high stagger ocapreasors are 0,400, >,400 and 10,300 respectively.

3.0 gg performance oaJLoulatione

In general, the performance calculations have been oarried out by similar methods to those given in ref. 1.

A diffuser efTiciency of 60# was assumed. This correaponda to * loss of 20jf of the outlet dynamic head in the diftuaer pipe, which is the minimum probable loss between the compressors and their oeubustion ohambers.

The curves obtained are plotted in i'ig. 1.

4*0 Conclusions

The curves of Fig. 1 sho-r typical performance curves for low, medium and high atagger compressors. Though only strictly applicable to the compressors that were designed, they probably show the changes that may be generally expected between compressor blades of various staggers. The slope of the pressure ratio curves becomes steeper and the value of the efficiency falls wore rapidly away from the design speed with an increase in stagger. The maximum efficiency, however, is furtner away from the surge point at the higher staggers.

tost of figures

figure 1, SK. 1642

9

Performance curves for low, medium and high stagger compressors.

Boferenoes.

SSL Author^

A. A. HoweU

Title etc

The present basis of axial flow compressor design. Part U. H.A.E. fieport No. B. 3961. (1942)

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D.C.S.Ä. D.G.T.D. D.Eng.R.0. D.D. T.B. (action Copy)

RTP/TIB (2U copies )

K.A.E. (Librarian) (3 oopiea) Bristol Aeroplane Co. (Mr. 9. M. Owner) De HavilXand Engine Co. (Mr. 16. 3. »foult) Rolla-*oycc! Ltd., Derby (Mr. A. G. Elliott)

H " " " (Dr. A. A. Griffith») • • " " (ar. T. C. Dickaon) " " " BarnoXdswick (Dr. S. G. Hooker)

Metropolitan-Vickers Bleat. Co. (Dr. D, M. Smith] Anuatrong Siddelay Motors Ltd. (Mr. f. P. Saxton) D. Napier & Son Ltd., (Mr. U. Salmons)

D.S.K. Engineer-in-Chief's Dept. (Cuidr. C. M. Hall) (2 oopiea) Admiralty Engineering laboratory (Capt. W. G. Cowlond)

" " (Mr. if. j. Kobinaon)

Turbo research Ltd., (Nr. J. Gould)

Mr. I. Berenblut (TE/H) M.A.P. (10 oopiea for G.T.O.C. Aero Panel)

Dr. Roxbee Cox A/Cdre. F. «hittle Mr. H. Constant W/C. G. Leea - T.B. Mr. 0. N. Walker - T.R. Mr. L. J. Cheshire - T.R. ii/C. A. tf. Kouks - H.T.O. - T.B.. e'/L. W.ü.P. Johnson - T.R. Mr. J. «5. Maofarlane Mr. A. B. HoweXl - T.B. Mr. P. Lloyd, Ayestook. Mr. H. Cohen, Pyvatook. Mr. D. H. MalXinson, Pyestook. Mr. A. P. Johnstone, lyes took. Mr. «.. G, ouith - iiero. File. Whetstone. Mr. S. Gray - j.ero. Pile, Pyestook. Section file , Technical Beoorda Authors Copy Pyestook Registry (2 oopiea) Spares.

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RESTRICTED ATI- 9669 1 TITLE: Calculated Performance Curves for Three Axial Flow Compressors with Low

Medium and High Stagger Blades DIVISION

^None) AUTHOR(S) : Mettam, Marjorie oaio. AcmcT NO,

M-1201

PUBUSHED BY : (Same) rttsusxuto AOtNcr no. (Same)

DAT!

March »41 DOC. CIA». Restr.

- COUNT1Y

Gt. Brit. lAMGUAOt

English PASES 4

lUUSTRATIONS

graphs ABSTRACT:

Performance estimates have been made for three typical compressors. Results are strictly applicable only to these compressors but they probably show the changes that may be generally expected between compressor blades of various staggers. Slope of pressure ratio curves become steeper and value of efficiency fails more rapidly away from design speed with increase in stagger. Maximum efficiency, however, is further away from surge point at higher staggers.

DISTRIBUTION: Copies of this report obtainable from CAPO DIVISION: Power Plants, Jet 6 Turbine (5) SECTION: Compressors (3)

ATI SHEET NO.: R-5-3-27

SUBJECT HEADINGS: Compressors, Axial (24300); Diffusors (30200)

Centre! Air Document» Oflka Wright-Pattorsen Air Force Base, Dayton, Ohio

AIR TECHNICAL INDEX

RESTRICTED

TITLE: Calculated Performance Curves for Three Axial Flow Compressors with Low Medium and High Stagger Blades *—•*

AUTHORIS) : Mettam, Marjorie (f\J 1 ORIG. AGENCY : National Gas Turbine Establishment, Whetstone, Leicester, PUBUSHED BY : (Same) • V~7

ATI- 9669

(None) CCTO. ACBKTT BO.

M-1201 PU3USMKO &S3CT CO.

(Same) DAT1 OOC CUSS. COUNTBT

March'4' Restr, Gt. Brit. lAHGUA«

English I 4 lUunOATIONS

graphs ABSTRACT:

Performance estimates have been made for three typical compressors. Results are strictly applicable only to these compressors but they probably show the changes that may be generally expected between compressor blades of various staggers. Slope of pressure ratio curves become steeper and value of efficiency falls more rapidly away from design speed with increase in stagger. Maximum efficiency, however, is further away from surge point at higher staggers.

DISTRIBUTION: Copies of this report obtainable from CAPO. niVICinM. TV..TS. Dlnntc Tat P. Tiii-hina iR\ SIIRICCT I DIVISION: Power Plants, Jet & Turbine (5) SECTION: Compressors (3) >

ATI SHEET NO.: R -5-3-27

SUBJECT HEADINGS: Compressors, Axial (24300); Diffusors (30200)

L- Central Air Documents Office

Wright-Pattanon Air Fore« Base, Dayton, Ohio AIR TECHNICAL INDEX

c £Ö 1Q501 dd 5 NCV 1953