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An axial compressor consists of alternating rows of rotating and stationary diffusers,<ref>https://archive.org/details/DTIC_ADA059784/page/n45/mode/2up,"All compression in engines requires a diffusion process", section 1.4.2.3</ref> each pair being a stage. These diffusers are diverging as necessary for subsonic flow.<ref>Supersonic flow is slowed in a converging duct as shown from the inlet lip to the shock trap bleed.[[File:J58 airflow at Mach 3.png|thumb|]]</ref> The channel formed by adjacent blades, amount of diffusion, is adjusted by varying their angle relative to tangential, known as stagger angle.<ref>https://ntrs.nasa.gov/citations/19650013744,"Aerodynamic Design of Axial-Flow Compressors", p. 126</ref> More diffusion gives a higher pressure ratio but flow in compressors is very susceptible to flow separation because it is going against a rising pressure (gas naturally flows from high to low pressure). Stage pressure ratio had increased by 2016 such that 11 stages could achieve 27:1 (GE9X high pressure compressor).<ref name="Dynamic Regulatory System" />
Low aspect ratio compressor blades, with their better efficiency both aerodynamically and structurally, were introduced in the 1950s turbojet the [[Tumansky R-11]], and subsequently examples of wide chord fan blades introduced in 1983 in the [[Garrett TFE731]]-5<ref>https://www.sae.org/publications/technical-papers/content/861837/, "Low Aspect Ratio Axial Flow Compressors: Why and What It Means", Wennerstrom, p. 11</ref> and in 1984 in the [[RB211]]-535E4<ref>https://www.worldcat.org/title/history-of-the-rolls-royce-rb211-turbofan-engine/oclc/909128142 {{Bare URL inline|date=August 2024}}</ref> and [[Pratt & Whitney Canada JT15D]]-5.<ref>https://asmedigitalcollection.asme.org/GT/proceedings/IGT1985/79429/V001T01A006/259190,"Development of a New Technology Small Fan Jet Engine", Boyd, ASME 85-IGT-139, p. 2</ref>
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