Engine inlet system with integral firewall seal
One embodiment is an inlet plenum assembly for a rotary aircraft that includes an inlet plenum defined on a first side by an inlet plenum wall and on a second side by a forward firewall assembly, the forward firewall assembly having an inlet aperture configured to receive a drive shaft to rotatably coupled to an engine; and a seal connected to the forward firewall assembly via a seal retainer disposed around a periphery of the inlet aperture. The forward firewall assembly may further include a forward firewall upper portion and a forward firewall lower portion, the forward firewall upper portion configured to removably seat to the forward firewall lower portion. The seal retainer may be attached to the forward firewall assembly via a plurality of bolts disposed around the periphery of the seal retainer. In some embodiments, the seal is connected to an inlet duct of the engine.
1. An inlet plenum assembly for a rotary aircraft, comprising:
an inlet plenum defined on a first side by an inlet plenum wall and on a second side by a forward firewall assembly, the forward firewall assembly having an inlet aperture configured to receive a drive shaft to rotatably coupled to an engine; and
a seal connected to the forward firewall assembly via a seal retainer disposed around a periphery of the inlet aperture;
wherein the forward firewall assembly comprises a forward firewall upper portion and a forward firewall lower portion, the forward firewall upper portion configured to removably seat to the forward firewall lower portion.
2. The inlet plenum assembly of claim 1 , wherein the seal retainer is attached to the forward firewall assembly via a plurality of bolts disposed around the periphery of the seal retainer.
3. The inlet plenum assembly of claim 1 , wherein the seal is connected to an inlet duct of the engine.
4. The inlet plenum assembly of claim 3 , wherein the engine inlet duct comprises a bellmouth.
5. The inlet plenum assembly of claim 3 , wherein the engine inlet duct comprises an integral flange feature to which the seal is connected.
6. The inlet plenum assembly of claim 5 , wherein the seal is connected to the integral flange feature via a seal retainer attached to the integral flange feature via a plurality of bolts disposed around a periphery of the integral flange feature.
7. The inlet plenum assembly of claim 1 , wherein a diameter of the inlet aperture is greater than a diameter of the engine inlet duct to provide a radial clearance between the engine and the firewall assembly.
8. The inlet plenum assembly of claim 1 , wherein a side of the seal to which the engine is attached and a side of the seal opposite the side of the seal to which the engine is attached are offset from one another to accommodate radial and axial movement of the engine relative to an airframe in which the engine is disposed.
9. The inlet plenum of claim 1 , wherein the seal is constructed of a flexible fireproof material.
10. A rotary aircraft, comprising:
an airframe;
an engine disposed within the airframe;
a driveshaft rotatably coupled to the engine;
an inlet plenum defined on a first side by an inlet plenum wall and on a second side by a forward firewall assembly, the forward firewall assembly having an inlet aperture configured to receive the drive shaft; and
a seal connected to the forward firewall assembly via a seal retainer disposed around a periphery of the inlet aperture;
wherein the forward firewall assembly comprises a forward firewall upper portion and a forward firewall lower portion, the forward firewall upper portion configured to removably seat to the forward firewall lower portion.
11. The rotary aircraft of claim 10 , wherein the seal retainer is attached to the forward firewall assembly via a plurality of bolts disposed around the periphery of the seal retainer.
12. The rotary aircraft of claim 10 , wherein the seal is connected to an inlet duct of the engine.
13. The rotary aircraft of claim 10 , wherein a diameter of the inlet aperture is greater than a diameter of the engine inlet duct to provide a radial clearance between the engine and the firewall assembly.
14. The rotary aircraft of claim 10 , wherein the seal is constructed of a flexible fireproof material.
15. A firewall for an inlet plenum assembly comprising:
a firewall upper portion and a firewall lower portion, the firewall upper portion configured to removably seat to the firewall lower portion;
an inlet aperture configured to receive a drive shaft to rotatably coupled to an engine; and
a flexible fireproof seal connected to the firewall via a seal retainer disposed around a periphery of the inlet aperture.
16. The firewall of claim 15 , wherein the seal is connected to an inlet duct of the engine.
17. The firewall of claim 16 , wherein the engine inlet duct comprises an integral flange feature to which the seal is connected.
18. The firewall of claim 15 , wherein a diameter of the inlet aperture is greater than a diameter of the engine inlet duct to provide a radial clearance between the engine and the firewall.