Method and control system for a turbomachine comprising a low-pressure electric machine and a high-pressure electric machine

Abstract

A method for controlling a turbomachine (100) comprising a low-pressure (LP) electric machine (M1) configured to inject or extract power from a low-pressure shaft (121) and a high-pressure (HP) electric machine (M2) configured to inject or extract power from a high-pressure shaft (122), the control method comprising steps of, during a steady-state (SR) operation of the turbomachine (100), controlling the extraction of main power (PU1) by the LP electric machine (M1) and controlling the injection of main power (PU1) by the HP electric machine (M2), and, during an acceleration of the turbomachine (100) operation, reducing the extraction of main power (PU1) by the LP electric machine (M1) and reducing the injection of main power (PU1) by the HP electric machine (M2). Abstract figure: Figure 4

Claims

8. Control system for a turbomachine (100) comprising a propulsion blower (110) positioned upstream of a gas generator and delimiting a primary flow and a secondary flow, said gas generator being traversed by the primary flow and comprising a low-pressure compressor (111), a high-pressure compressor (112), a combustion chamber (113), a high-pressure turbine (114) and a low-pressure turbine (115), said low-pressure turbine (115) being connected to said low-pressure compressor (111) by a low-pressure shaft (121) and said high-pressure turbine (114) being connected to said high-pressure compressor (112) by a high-pressure shaft (122), the turbomachine (100) comprising a low-pressure (LP) electric machine (M1) configured to inject or withdraw power on the low-pressure shaft (121) and a high-pressure (HP) electric machine (M2) configured to inject or withdraw power on the high-pressure shaft (122),The control system comprises: • a computer (200) configured to determine a control fuel flow rate (WFcmd), a first control power on the low-pressure (LP) electric machine (M1) and a second control power on the high-pressure (HP) electric machine (M2), the computer (200) being configured to: • During a stabilized speed (SR) of the turbomachine (100), command a main power draw (PU1) on the low-pressure shaft (121) by the LP electric machine (M1) and command an injection of the main power (PU1) on the high-pressure shaft (122) by the HP electric machine (M2), and • During an accelerated speed (AR) of the turbomachine (100), reduce the main power draw (PU1) by the LP electric machine (M1) and reduce the injection of the main power (PU1) by the HP electric machine (M2).

9. Assembly of a turbomachine (100) and a control system according to claim 8.

10. Aircraft comprising an assembly according to claim 9. [Fig. 1] FIG. 1 [Fig. 2] FIG. 2 [Fig. 3] MAN [Fig. 4] 200 FIG. 4 [Fig. 5] FIG. 5 [Fig. 6] FIG. 6 [Fig. 7] kW FIG. 7 [Fig. 8] FIG. 8

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