Aeronautical power system
An acronautical power system is provided. The system includes a first electric machine having an EM1 channel; a second electric machine having an EM2 channel; a first converter box in electric connection with the EM1 channel and the EM2 channel.
1 . An aeronautical power system comprising:
a first electric machine comprising an EM1 channel;
a second electric machine comprising an EM2 channel;
a first converter box in electric connection with the EM1 channel and the EM2 channel, wherein the first converter box includes an EM1 channel AC/DC converter and an EM2 channel AC/DC converter;
a common capacitor bank; and
an EMI filter arranged in series with the common capacitor bank, wherein the EM1 channel AC/DC converter and the EM2 channel AC/DC converter are each in electrical connection with EMI filter through the common capacitor bank.
2 . The aeronautical power system of claim 1 , wherein the first electric machine has a first power rating, and wherein the second electric machine has a second power rating that is different from the first power rating.
3 . The aeronautical power system of claim 1 , wherein the first electric machine is a low pressure spool electric machine configured to rotate with a low pressure spool of an engine when the aeronautical power system is integrated with the engine, and wherein the second electric machine is a high pressure spool electric machine configured to rotate with a high pressure spool of the engine when the aeronautical power system is integrated with the engine.
4 . The aeronautical power system of claim 1 , further comprising:
an EM1 first channel isolator in electrical connection with the EM1 channel AC/DC converter and the common capacitor bank at a location between the EM1 channel AC/DC converter and the common capacitor bank.
5 . The aeronautical power system of claim 4 , further comprising:
an EM1 channel local capacitor bank in electrical connection with the EM1 channel AC/DC converter and the EM1 first channel isolator at a location between the EM1 channel AC/DC converter and the EM1 first channel isolator.
6 . The aeronautical power system of claim 5 , wherein the EM1 channel local capacitor bank defines an electrical capacitance rating lower than a capacitance rating of the common capacitor bank.
7 . The aeronautical power system of claim 1 , further comprising:
an EM2 channel isolator in electrical connection with the EM2 channel AC/DC converter and the common capacitor bank at a location between the EM2 channel AC/DC converter and the common capacitor bank.
8 . The aeronautical power system of claim 1 , wherein the common capacitor bank is housed within the first converter box.
9 . The aeronautical power system of claim 1 , further comprising:
a PDMU, wherein the EM1 channel AC/DC converter and the EM2 channel AC/DC converter are in electrical connection with the PDMU through a single DC power link.
10 . The aeronautical power system of claim 9 , wherein the PDMU includes a first section and a second section, wherein the first section of the PDMU is housed in the first converter box.
11 . The aeronautical power system of claim 1 , wherein the EMI filter is housed in the first converter box.
12 . The aeronautical power system of claim 1 , wherein the EM1 channel is an EM1 first channel and the first electric machine further comprises an EM1 second channel, wherein the EM2 channel is an EM2 first channel and the second electric machine further comprises an EM2 second channel, and wherein the aeronautical power system further comprises:
a second converter box in electric connection with the EM1 second channel and the EM2 second channel.
13 . The aeronautical power system of claim 12 , wherein the first converter box comprises a first cold plate assembly, and wherein the second converter box comprises a second cold plate assembly.
14 . The aeronautical power system of claim 13 , further comprising:
a first thermal loop driven by the first electric machine and in thermal communication with both the first cold plate assembly and the second cold plate assembly; and
a second thermal loop driven by the second electric machine and also in thermal communication with both the first cold plate assembly and the second cold plate assembly.
15 . A hybrid-electric propulsion system comprising:
a turbomachine comprising a first rotatable shaft and a second rotatable shaft; and
an aeronautical power system comprising:
a first electric machine comprising an EM1 channel, the first electric machine rotatable with the first rotatable shaft of the turbomachine;
a second electric machine comprising an EM2 channel, the second electric machine rotatable with the second rotatable shaft of the turbomachine;
a first converter box in electric connection with the EM1 channel and the EM2 channel, wherein the first converter box includes an EM1 channel AC/DC converter and an EM2 channel AC/DC converter;
a common capacitor bank; and
an EMI filter arranged in series with the common capacitor bank, wherein the EM1 channel AC/DC converter and the EM2 channel AC/DC converter are each in electrical connection with EMI filter through the common capacitor bank.
16 . An aeronautical power system comprising:
a first electric machine comprising an EM1 channel;
a second electric machine comprising an EM2 channel;
a first converter assembly in electric connection with the EM1 channel and the EM2 channel, wherein the first converter assembly includes an EM1 channel AC/DC converter and an EM2 channel AC/DC converter;
a PDMU having a first section, wherein the first section is in electrical connection with the first converter assembly through a single DC power link;
a common capacitor bank; and
an EMI filter arranged in series with the common capacitor bank, wherein the EM1 channel AC/DC converter and the EM2 channel AC/DC converter are each in electrical connection with EMI filter through the common capacitor bank.