Air intake for an aircraft propulsion system engine assembly
An engine assembly for an aircraft propulsion system includes a gas turbine engine, a gearbox, and a first drive shaft. The gas turbine engine includes an engine output shaft, an air intake, and a compressor. The air intake includes an air intake body forming an air inlet, an air outlet, and an air plenum extending between and connecting the air inlet and the air outlet. The air plenum extends circumferentially about the engine output shaft between and to a first circumferential end of the air intake and a second circumferential end of the air intake. The first circumferential end and the second circumferential end form a circumferential gap. The compressor is connected in fluid communication with the air intake. The gearbox includes a gear assembly operably connected to the engine output shaft. The first drive shaft is operably connected to the gear assembly. The first drive shaft extends through the circumferential gap.
1. An engine assembly for an aircraft propulsion system, the engine assembly comprising:
a gas turbine engine including:
an engine output shaft configured for rotation about a first rotational axis,
an air intake including an air intake body forming an air inlet, an air outlet, and an air plenum extending between and connecting the air inlet and the air outlet in fluid communication, the air plenum extends circumferentially about the engine output shaft between and to a first circumferential end of the air intake and a second circumferential end of the air intake, the first circumferential end and the second circumferential end enclosing the air plenum opposite the air inlet relative to the first rotational axis, and the first circumferential end and the second circumferential end form a circumferential gap outside of the air intake and circumferentially between the first circumferential end and the second circumferential end, the circumferential gap located opposite the air inlet relative to the first rotational axis, and
a compressor connected in fluid communication with the air intake at the air outlet;
a gearbox including a gear assembly operably connected to the engine output shaft; and
a first drive shaft operably connected to the gear assembly, the first drive shaft is rotatable about a second rotational axis, the second rotational axis is radially offset from the first rotational axis, and the first drive shaft extends along the second rotational axis through the circumferential gap.
2. The engine assembly of claim 1 , wherein at least a portion of the first drive shaft is disposed radially inside the air intake body.
3. The engine assembly of claim 1 , wherein the air intake further includes a screen, and the screen extends circumferentially within the air plenum from the first circumferential end to the second circumferential end.
4. The engine assembly of claim 3 , wherein at least a portion of the first drive shaft is disposed radially inside the screen.
5. The engine assembly of claim 1 , further comprising a second drive shaft operably connected to the gear assembly, the second drive shaft is rotatable about a third rotational axis, and the third rotational axis is radially offset from the first rotational axis.
6. The engine assembly of claim 5 , wherein the third rotational axis and the second rotational axis are colinear.
7. The engine assembly of claim 1 , wherein the air intake body forms the air inlet at a first circumferential position of the air intake.
8. The engine assembly of claim 1 , wherein the air intake includes an end strut forming the first circumferential end and the second circumferential end.
9. The engine assembly of claim 1 , wherein the air intake body includes an outer radial wall portion, and the outer radial wall portion is radially offset from the air outlet.
10. The engine assembly of claim 9 , wherein a radial distance between the outer radial wall portion and the air outlet decreases in a circumferential direction from:
the air inlet to the first circumferential end; and
the air inlet to the second circumferential end.
11. The engine assembly of claim 1 , wherein the air intake further includes at least one guide strut disposed within the air plenum.
12. The engine assembly of claim 1 , wherein the engine assembly is enclosed by a housing.
13. The engine assembly of claim 1 , wherein the air inlet is disposed radially outward of the air intake.
14. An engine assembly for an aircraft propulsion system, the engine assembly comprising:
a gas turbine engine including:
an air intake including an air intake body extending circumferentially about an axis, the air intake body forms an air inlet, an air outlet, and an air plenum extending between and connecting the air inlet and the air outlet in fluid communication, the air intake body forms the air inlet at a first circumferential position of the air intake, the air plenum extends circumferentially about the axis between and to a first circumferential end of the air intake and a second circumferential end of the air intake, the first circumferential end and the second circumferential end form a circumferential gap outside of the air intake and circumferentially between the first circumferential end and the second circumferential end, and the first circumferential end, the second circumferential end, and the circumferential gap disposed at a second circumferential position of the air intake circumferentially opposite the first circumferential position;
a compressor connected in fluid communication with the air intake at the air outlet; and
a drive shaft, the drive shaft is rotatable about a rotational axis, the rotational axis is radially offset from the axis, and the drive shaft extends along the rotational axis through the circumferential gap.
15. The engine assembly of claim 14 , wherein at least a portion of the drive shaft is disposed radially inside the air intake body.
16. The engine assembly of claim 14 , wherein the air intake further includes a screen, and the screen extends circumferentially within the air plenum from the first circumferential end to the second circumferential end.
17. The engine assembly of claim 16 , wherein at least a portion of the drive shaft is disposed radially inside the screen.