SRV open rotor with core inlet forward of rotor

Patent metadata

Field	Value
Publication number	US-12466544-B1
Application number	US-202418661272-A
Country	US
Kind code	B1
Filing date	May 10, 2024
Priority date	May 10, 2024
Publication date	Nov 11, 2025
Grant date	Nov 11, 2025

Abstract

An aircraft propulsion system includes a rotor hub, rotor blades, a rotating frame, and a low-pressure compressor. The rotor hub is configured to rotate about a central axis. The rotor blades are arranged around the rotor hub. Each of the rotor blades is configured to rotate about a radial axis of the rotor hub. The rotating frame is positioned between the rotor hub and the plurality of rotor blades. The rotating frame is configured to allow air to pass without interference of the rotor blades. The low-pressure compressor is configured to receive the air passing through the rotating frame.

First claim

What is claimed is:

1. An aircraft propulsion system comprising:
a rotor hub configured to rotate about a central axis;
a plurality of rotor blades arranged around the rotor hub, each of the rotor blades configured to rotate about a radial axis of the rotor hub;
a rotating frame positioned between the rotor hub and the plurality of rotor blades, the rotating frame defining a core inlet located forward of the plurality of rotor blades for receiving air to allow air to pass without interference of the rotor blades; and
a low-pressure compressor configured to receive the air passing through the rotating frame.

2. The aircraft propulsion system of claim 1 , wherein the rotating frame includes a plurality of struts supporting a rotating inlet splitter.

3. The aircraft propulsion system of claim 2 , further comprising a rotor spar for each of the rotor blades, the rotor spar configured to connect a rotor blade to the rotor hub through each strut.

4. The aircraft propulsion system of claim 3 , wherein the rotor hub comprises variable pitch rotor blades.

5. The aircraft propulsion system of claim 1 , further comprising a static frame configured to support the rotor hub through bearings and a fan drive gear system and guide air from the rotating frame towards the low-pressure compressor.

6. The aircraft propulsion system of claim 5 , wherein the static frame includes struts supporting the fan drive gear system and the bearings supporting the rotor hub.

7. The aircraft propulsion system of claim 1 , further comprising a spinner configured to direct air towards the core inlet of the rotating frame.

8. An apparatus comprising:
a rotor hub configured to rotate about a central axis;
a plurality of rotor blades arranged around the rotor hub, each of the rotor blades configured to rotate about a radial axis of the rotor hub; and
a rotating frame positioned between the rotor hub and the plurality of rotor blades, the rotating frame defining a core inlet located forward of the plurality of rotor blades for receiving air to allow air to pass without interference of the rotor blades, wherein the rotating frame includes a plurality of struts supporting a rotating inlet splitter.

9. The apparatus of claim 8 , further comprising a rotor spar for each of the rotor blades, the rotor spar configured to connect a rotor blade to the rotor hub through each strut.

10. The apparatus of claim 9 , wherein the rotor hub comprises variable pitch rotor blades.

11. The apparatus of claim 8 , further comprising a static frame configured to support the rotor hub through bearings and a fan drive gear system and guide air from the rotating frame towards the low-pressure compressor.

12. The apparatus of claim 11 , wherein the static frame includes struts supporting the fan drive gear system and the bearings supporting the rotor hub.

13. The apparatus of claim 8 , further comprising a spinner configured to direct air towards the core inlet of the rotating frame.

14. A method for an aircraft propulsion system including a rotor hub configured to rotate about a central axis, a plurality of rotor blades arranged around the rotor hub, each of the rotor blades configured to rotate about a radial axis of the rotor hub, and a rotating frame positioned between the rotor hub and the plurality of rotor blades, the method comprising:
passing air through a core inlet defined forward of the plurality of rotor blades by the rotating frame to enable the air to flow through the core inlet without interference of the rotor blades; and
receiving the air passing through the core inlet in the rotating frame in a low-pressure compressor.

15. The method of claim 14 , wherein the rotating frame includes a plurality of struts supporting a rotating inlet splitter.

16. The method of claim 15 , further comprising:
rotating the rotor blades of the rotor hub through each strut, wherein the rotor hub comprises variable pitch rotor blades.

17. The method of claim 16 , wherein a rotor spar for each of the rotor blades connects a rotor blade to the rotor hub through each strut.

18. The method of claim 14 , further comprising:
passing the air from the core inlet of the rotating frame through a static frame supporting the rotor hub through bearings and a fan drive gear system,
wherein the static frame includes struts supporting the fan drive gear system and the bearings supporting the rotor hub.

19. The method of claim 14 , further comprising:
directing, using a spinner, air towards the core inlet of the rotating frame.

Assignees

• Rtx Corp

Inventors

• Morton Jeffrey T
• Voytovych Dmytro M

Classifications

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D7/00

  Rotors with blades adjustable in operation; Control thereof (for reversing F01D1/30) · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• B64C11/14

  Spinners · CPC title

• F05D2260/74

  by turning around an axis perpendicular the rotor centre line · CPC title