compressor inlet वाक्य
उदाहरण वाक्य
मोबाइल
- Compressor inlet cooling increases the aerodynamic speed and flow and thrust.
- The vaporized refrigerant flows to the compressor inlet to complete the cycle.
- Compressor inlet cooling is used in the first case.
- The resulting refrigerant vapor returns to the compressor inlet to complete the thermodynamic cycle.
- This accessory layout, as used on centrifugal engines, restricted the area available for compressor inlet air.
- Figure 2 indicates how efficiency changes with an increase in the heat addition temperature for a constant compressor inlet temperature.
- Studying these two plots further we see that the pressure rises between the compressor inlet ( station 1 ) and compressor exit ( station 2 ).
- A compressor map shows that the airflow reduces with increasing compressor inlet temperature although the compressor is still running at maximum RPM ( but reduced aerodynamic speed ).
- Any boost pressure produced by the secondary turbocharger during the transitional stage is redirected to the atmospheric side of the compressor inlet ( between the turbos and air filter ).
- The engine had its starter and accessories ( fuel control, fuel pump, oil pumps, hydraulic pump, RPM generator ) mounted in the centre of the compressor inlet.
- An engine, uprated from the J47, was required for the F-86H . The mass flow was increased by relocating accessories from the centre of the compressor inlet to the underside of the engine.
- During transition, fuel to the gas generator was not reduced, as in the Griffon 02 when the external flow was burning, but thrust available from the gas generator automatically decreased as a consequence of operating at a fixed turbine temperature limit and with increasing compressor inlet temperature.
- Adams opines that the designers of ML-1 made several incorrect decisions, including adding an unnecessary recuperator to enhance efficiency, using a calandria-based water-tube fission heat source unproven in the " real world ", using nine atmospheres of pressure at the compressor inlet that saved space but required a custom-built turbine rather than one designed for atmospheric pressures, placing insulating foil within the gas piping to improve efficiency ( the foil later broke off and contaminated the closed loop with its flecks, causing deflecking problems for engineers ), and using custom-built, first-of-a-kind components instead of using commercially proven aircraft or power generation derived turbines.
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