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A CNC-milled, single piece axial compressor blisk. A blisk (portmanteau of bladed disk) is a turbomachine component comprising both rotor disk and blades as a single part instead of a disk assembled with individual removable blades.
This page is an incomplete list of orbital rocket engine data and specifications. Current, upcoming, and in-development rocket engines ... 338 (SL) [18] 1,098,000 ...
In this respect, a digital AIP is a digital version of the paper AIP, usually available in PDF format, while an electronic AIP is available in PDF as well as other formats, more suitable for reading on the screen and for electronic data exchange. Many countries around the world provide digital AIPs either on CD-ROM subscription or on a Web site.
The YF119-PW-614 on the X-32 had a pitch-axis thrust vectoring nozzle and valves can redirect the engine exhaust and bleed air to provide direct lift, similar to the Pegasus engine on the Harrier. In contrast, YF119-PW-611 on the X-35 had a round axisymmetric nozzle that can swivel downwards while the low-pressure spool drives a lift fan that's ...
Workshare on the joint venture's first engine, the V2500, was divided between the constituent aero-engine companies. Rolls-Royce based the high pressure compressor on a scale-up of the RC34B eight stage research unit used in the RB401-06 Demonstrator Engine, but with a zero-stage added at the front and a tenth stage added to the rear. [1]
This is the case on many large aircraft such as the 747, C-17, KC-10, etc. If you are on an aircraft and you hear the engines increasing in power after landing, it is usually because the thrust reversers are deployed. The engines are not actually spinning in reverse, as the term may lead you to believe.
The Tumansky R-29 is a Soviet turbojet aircraft engine that was developed in the early 1970s. [1] It is generally described as being in the "third generation" of Soviet gas turbine engines which are characterized by high thrust-to-weight ratios and the use of turbine air cooling.
The PW 300 series has been developed in partnership with MTU who are responsible for the low pressure turbine. The first variant, the PW305A, has the following configuration and was designed with a core flexible enough for engines with take-off thrusts from 20 kN to 31 kN (4,500 to 7,000 lb): a single-stage fan driven by a three-stage low pressure turbine, supercharging a four-stage axial ...