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A variable pitch fan is similar in concept to that of a variable-pitch propeller and involves progressively reducing the pitch (or blade angle) of the fan on a turbofan as the engine is throttled. Although variable pitch fans are used in some industrial applications, the focus of this article is on their use in turbofan engines .
The Turbomeca Astafan is a single-spool, variable-pitch turbofan engine developed from the Turbomeca Astazou. [1]: 553 [2]: 932 Despite successful flight-testing, an efficient, quiet and clean design (compared to turbojets and conventional turbofans) [1]: 554–555 [3]: 1648 [4]: 1872 and some commercial interest, [5]: 1683 the Astafan never entered series production.
A geared, variable pitch fan, replaced the first stage of the low pressure (LP) compressor. A modest fan pressure ratio, consistent with the high bypass ratio, meant a low fan tip speed could be employed. A low hot jet velocity was another major design feature.
Propulsive efficiency comparison for various gas turbine engine configurations. In the 1970s, Hamilton Standard described its propfan as "a small diameter, highly loaded multiple bladed variable pitch propulsor having swept blades with thin advanced airfoil sections, integrated with a nacelle contoured to retard the airflow through the blades thereby reducing compressibility losses and ...
In the 1970s, Rolls-Royce/SNECMA tested a M45SD-02 turbofan fitted with variable-pitch fan blades to improve handling at ultralow fan pressure ratios and to provide thrust reverse down to zero aircraft speed.
The UltraFan is a geared turbofan with a variable pitch fan system that promises at least 25% efficiency improvement. [84] The UltraFan aims for a 15:1 bypass ratio and 70:1 overall pressure ratio. [85] The Ultrafan keeps the Advance core, but also contains a geared turbofan architecture with variable-pitch fan blades.
Review of these design studies in June indicated the design of such a high-bypass engine as a single-rotation, geared fan configuration with variable blade pitch. The fan diameter was expected to range from 108 to 118 in while having a bypass ratio of 18:1 to 20:1. Availability of the engine was estimated between 1992 and 1994. [1]
COBRA was a European Union-Russia cooperative program to study an ultra-high bypass ratio (UHBR) counter-rotating turbofan (CRTF) that was similar to the NK-93. Participating organizations included Kuznetsov, CIAM, Russian propeller manufacturer Aerosila , French engine maker Safran (Snecma), the French aerospace laboratory ( ONERA ), and the ...
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