Turbocompressor unit for an aircraft propulsion system

1 . An aircraft propulsion system comprising:

a turbocompressor unit including a compressor, a turbine, a rotational assembly, and a static structure, the rotational assembly rotatable about a rotational axis, the rotational assembly including a bladed compressor rotor of the compressor, a bladed turbine rotor of the turbine, and a shaft, the shaft interconnecting the bladed compressor rotor and the bladed turbine rotor, the static structure forming a first cavity and a second cavity, the first cavity connected in fluid communication with the compressor, the second cavity disposed at the turbine;

an engine exhaust assembly including an annular scroll disposed between the first cavity and the second cavity, the annular scroll including a scroll body and a plurality of hollow stator vanes, the scroll body forming a flow channel connected in fluid communication with the turbine, the plurality of hollow stator vanes disposed within the flow channel and circumferentially distributed about the rotational axis; and

a tube assembly including a tubular body, the tubular body extending along a tube axis between and to a first axial tube end and a second axial tube end, the tubular body extending through one of the plurality of hollow stator vanes between and to the first cavity and the second cavity, the tubular body forming an internal passage extending along the tube axis from the first axial tube end to the second axial tube end, the internal passage connecting the first cavity in fluid communication with the second cavity.

2 . The aircraft propulsion system of claim 1 , wherein the scroll body extends axially between and to a first axial scroll end and a second axial scroll end, and the scroll body forms a portion of the second cavity at the second axial scroll end.

3 . The aircraft propulsion system of claim 2 , wherein the tubular body is mounted to the scroll body at the second axial scroll end.

4 . The aircraft propulsion system of claim 2 , wherein the scroll body forms a third cavity at the first axial scroll end, and the tubular body extends through the third cavity to the first cavity.

5 . The aircraft propulsion system of claim 4 , wherein the third cavity is a dead cavity.

6 . The aircraft propulsion system of claim 1 , wherein the tube assembly further includes a sealing body mounted on the static structure at the first cavity, the sealing body includes an inner sealing surface extending circumferentially about the tube axis, and the first axial tube end is disposed within the sealing body at the inner sealing surface.

7 . The aircraft propulsion system of claim 6 , wherein the tube assembly further includes a seal disposed at the first axial tube end, and the seal is disposed in sealing engagement with the inner sealing surface.

8 . The aircraft propulsion system of claim 7 , wherein the first axial tube end is axially translatable relative to the inner sealing surface along the tube axis.

9 . The aircraft propulsion system of claim 1 , further comprising an engine including an exhaust port, and the flow channel forms a portion of a combustion gas flow path from the exhaust port to the turbine.

10 . The aircraft propulsion system of claim 1 , wherein the static structure further includes a bearing assembly mounted to rotationally support the shaft, and the bearing assembly is connected in fluid communication with the first cavity.

11 . An aircraft propulsion system comprising:

a turbocompressor unit including a compressor, a turbine, a rotational assembly, and a static structure, the rotational assembly rotatable about a rotational axis, the rotational assembly including a bladed compressor rotor of the compressor, a bladed turbine rotor of the turbine, and a shaft, the shaft interconnecting the bladed compressor rotor and the bladed turbine rotor, the static structure forming a first cavity and a second cavity, the first cavity connected in fluid communication with the compressor, the second cavity disposed at the turbine;

an engine exhaust assembly including an annular scroll axially between the compressor and the turbine, the annular scroll including a scroll body and a plurality of hollow stator vanes, the scroll body including a first axial side wall, a second axial side wall, and an outer wall forming a flow channel of the annular scroll, the flow channel connected in fluid communication with the turbine, the plurality of hollow stator vanes extending between and to the first axial side wall and the second axial side wall; and

a tube assembly including a tubular body, the tubular body extending along a tube axis between and to a first axial tube end and a second axial tube end, the second axial tube end mounted to the second axial side wall, the tubular body extending through one of the plurality of hollow stator vanes between and to the first cavity and the second cavity, the tubular body forming an internal passage extending along the tube axis from the first axial tube end to the second axial tube end, the internal passage connecting the first cavity in fluid communication with the second cavity.

12 . The aircraft propulsion system of claim 11 , wherein the static structure includes a turbine case circumscribing the bladed turbine rotor, and the second cavity is disposed radially outward of the turbine case.

13 . The aircraft propulsion system of claim 11 , wherein the scroll body forms a third cavity, and the tubular body extends through the third cavity to the first cavity.

14 . The aircraft propulsion system of claim 13 , wherein the third cavity is a dead cavity.

15 . The aircraft propulsion system of claim 11 , wherein the static structure further includes a bearing assembly mounted to rotationally support the shaft, and the bearing assembly is connected in fluid communication with the first cavity.

16 . An aircraft propulsion system comprising:

a turbocompressor unit including a compressor, a turbine, a rotational assembly, and a static structure, the rotational assembly rotatable about a rotational axis, the rotational assembly including a bladed compressor rotor of the compressor, a bladed turbine rotor of the turbine, and a shaft, the shaft interconnecting the bladed compressor rotor and the bladed turbine rotor, the static structure forming a first cavity and a second cavity, the first cavity connected in fluid communication with the compressor, the second cavity disposed at the turbine;

an engine exhaust assembly including an annular scroll disposed between the first cavity and the second cavity, the annular scroll including a scroll body and a plurality of hollow stator vanes, the scroll body forming a flow channel connected in fluid communication with the turbine, the plurality of hollow stator vanes disposed within the flow channel and circumferentially distributed about the rotational axis; and

a tube assembly including a tubular body, a seal, and a sealing body, the tubular body extending along a tube axis between and to a first axial tube end and a second axial tube end, the tubular body extending through one of the plurality of hollow stator vanes between and to the first cavity and the second cavity, the tubular body forming an internal passage extending along the tube axis from the first axial tube end to the second axial tube end, the internal passage connecting the first cavity in fluid communication with the second cavity, the tubular body forms a seal groove at the first axial tube end, the seal is disposed in the seal groove, the sealing body is mounted on the static structure at the first cavity, the seal is sealingly engaged with the sealing body, and the first axial tube end is moveable within the sealing body.

17 . The aircraft propulsion system of claim 16 , wherein the tubular body is mounted to the scroll body.

18 . The aircraft propulsion system of claim 16 , wherein the scroll body extends axially between and to a first axial scroll end and a second axial scroll end, and the scroll body forms a portion of the second cavity at the second axial scroll end.

19 . The aircraft propulsion system of claim 18 , wherein the tubular body is mounted to the scroll body at the second axial scroll end.

20 . The aircraft propulsion system of claim 16 , further comprising an engine including an exhaust port, and the flow channel forms a portion of a combustion gas flow path from the exhaust port to the turbine.