Improvement for rotorcraft equipped with turboshaft engines

A technology of rotorcraft and turbine engine, applied in aircrafts, engine components, machines/engines, etc., can solve the problems of high fuel consumption rate, money consumption, time consumption, etc., and achieve the effect of reducing fuel consumption rate and increasing driving power

Active Publication Date: 2009-04-29
EUROCOPTER
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] Although in some cases it can be done to some extent by adding an engine and by changing the drivetrain accordingly, matching the existing helicopter to the requirements / missions requiring a higher power rating, in order to change the drivetrain, Requires specialized design, development, and testing, which is very time-consuming and expensive
[0011] That kind of practice can easily be done by using several engines with small single power, but unfortunately, the fuel consumption rate of small single power engines is higher than that of single high power engines.
[0012] Also, the design, development, and testing of engines of appropriate power, especially high-power engines, are also time-consuming and costly.

Method used

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  • Improvement for rotorcraft equipped with turboshaft engines
  • Improvement for rotorcraft equipped with turboshaft engines
  • Improvement for rotorcraft equipped with turboshaft engines

Examples

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Embodiment Construction

[0036] Reference figure 2 Up to 6, the present invention relates to helicopters 10 and other rotorcraft, on which at least one lift and propulsion rotor 11 equipped with blades 12 is driven by one or more turbine engines 13 to rotate about a substantially vertical axis 14.

[0037] The main gearbox (MGB) connects the output shafts 15 and 16 of each engine to the shaft 17 of the main rotor. This gearbox especially includes a reducer (see Figure 5 ).

[0038] Such as figure 1 As shown, each engine includes an internal compressor 130 and a first turbine 131 constrained to rotate with the internal compressor 130. The engine also includes a free turbine 132, which is downstream of the first turbine relative to the direction 133 of gas flow through the engine.

[0039] The free turbine generates drive torque, which is transmitted by the shaft 134 of the free turbine, and then transmitted by the output shaft 15 of the engine via the reducer 135. This output shaft runs along the line pa...

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PUM

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Abstract

A rotorcraft (10) has a main rotor (11), a turbine engine (13), and a transmission mechanism (MGB) coupled to the rotor and to the engine to enable the engine to drive the rotor. The engine has a free turbine (132) connected to the transmission mechanism (MGB) by a shaft (15, 15a, 15b, 16, 18). The rotorcraft includes an external compressor (19) arranged to be driven by the free turbine (132) or by an electric motor, together with an air-transport duct (21) connecting the external compressor (19) to the engine so as to deliver the air that has been compressed by the external compressor to the inlets (22) of the engine.

Description

Technical field [0001] The present invention relates to improvements that can be used on rotorcraft equipped with one or more turbine engines. [0002] The technical field of the present invention is helicopter manufacturing. Background technique [0003] The rotorcraft has at least one rotor equipped with fins, sometimes called the main rotor, which provides lift and propulsion to the rotorcraft when it rotates. [0004] A rotorcraft has one or two or three engines for driving the main rotor, and possibly an anti-torque rotor, as well as various accessories (especially AC engines and one or several pumps). [0005] The transmission mechanism, also known as the main gear box (MGB), connects the output shaft of the engine to the shaft of the main rotor, especially the transmission mechanism including a reducer. Patent documents US 3 002 710, US 3 255 825 and US 4 811 627 all exemplify such transmission mechanisms. [0006] Each engine has an axial and / or centrifugal compressor, wh...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B60C27/12B64D27/10F02C3/04F02C7/36
CPCF02C7/143B64D33/02Y02T50/675B64D27/10F02C3/103F05B2220/309F05D2220/329F02C7/36B64C27/12B64D35/02Y02T50/60B64C27/18
Inventor B·瑟坦
Owner EUROCOPTER
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