Steady-state Performance of J85-21 Compressor at 100 Percent of Design Speed with and Without Interstage Rake Blockage PDF Download
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Category :
Languages : en
Pages : 40
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Author:
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Category :
Languages : en
Pages : 40
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Category : Aeronautics
Languages : en
Pages : 794
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Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
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Category : Aeronautics
Languages : en
Pages : 750
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Author:
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Category : Aeronautics
Languages : en
Pages : 736
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A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
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Category : Science
Languages : en
Pages : 898
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Category : Government reports announcements & index
Languages : en
Pages : 944
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Author: Edward J. Milner
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Category : Airplanes
Languages : en
Pages : 40
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The results presented are of a series of experimental tests in which a J85-13 turbojet engine was subjected to both distorted and undistorted inlet total pressure conditions. A distinctive feature of the data base obtained is that it includes compressor interstage information not previously recorded for a J85-13 engine. Each of the eight compressor stages was instrumented to obtain the characteristics of the individual stages for undistorted inlet conditions, and these data are documented in the report along with the undistorted compressor overall performance. Also included in the report is the overall performance of the compressor exposed to 14 different distorted-inlet conditions - 10 circumferential patterns and 4 radial patterns. The distortion patterns were introduced using screens that spoiled from 8 to 50 percent of the compressor face area; the distortion screen density, or the area blocked by the screen wire per unit area of screen, varied from 26 to 69 percent.
Author: Edward J. Milner
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Category : Compressors
Languages : en
Pages : 36
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Book Description
The parallel compressor concept was studied using a compressor model based on the overall clean-inlet performance map obtained from experimental tests in an altitude chamber using a General Electric J85-13 turbojet engine. The model, which includes a static-pressure balance calculation at compressor discharge, was exercised at conditions corresponding to 10 different screen-induced distortion patterns included in the experimental data base. The spoiled area of these patterns ranged from 30 deg to 180 deg, and the distortion screen density, or the area blocked by the screen wire per unit area of screen, varied from 26 to 69 percent. The study indicates that at the higher corrected speeds, the analytical surge lines obtained are good representations of the corresponding experimental surge lines and are independent of distortion angle or distortion angle or distortion level.
Author: Willard R. Westphal
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Category : Axial flow compressors
Languages : en
Pages : 66
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A six-stage axial-flow compressor with a tip speed of 550 feet per second and a flat operating characteristics at constant speed has been designed and tested. It was designed for a constant power input per pound of flow in expectation that this would result in a wider mass-flow operating range at a given stagnation-presssure ratio. The design specific weight flow was 21.3 pounds per second per square foot of frontal area at atmospheric discharge with a stagnation-pressure ratio of 3.25 and an inlet hub-tip radius ratio of 0.7. Several configurations consisting of various blade setting angles and solidities were tested. Tests showed that the design flow, pressure ratio, and flat operating characteristic were obtained over a range of 10 percent of design flow at a peak efficiency of 82 percent for design conditions. The compressor had a possible immediate application for air removal from a large slotted-throat transonic wind tunnel, but the design theory could apply to any low-speed industrial compressor or second spool of a turbojet engine.
Author: Roy D. Hager
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ISBN:
Category : Compressors
Languages : en
Pages : 24
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