Vectoring transition duct for turbine engine

• US 7,854,112 B2
• Filed: 12/01/2004
• Issued: 12/21/2010
• Est. Priority Date: 12/01/2004
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Roberge, Gary D.
• Primary Examiner(s): Cuff; Michael
• Assistant Examiner(s): NGUYEN, ANDREW H
• Application Number:
  US11/719,477
• Publication Number:
  US 20090142184A1
• Time in Patent Office: 2,211 Days
• Field of Search: 60/394.3, 602/261, 602/69, 602/62, 602/28, 602/30, 607/70, 607/71, 602/42, 415/155, 415/160, 415/161, 415/167, 415/77, 244/23.D, 239/265.19, 416/175, 416/203, 416/193.R
• US Class Current: 60/226.1
• CPC Class Codes: F02K 1/006 within one plane only
• CPC Class Codes: F02K 3/068 being characterised by a short axial length relative to the diameter

Abstract

A transition duct (112) is provided at the outlet of a turbine engine. The transition duct transitions the outlet of the tip turbine engine (10) from round to rectangular. The transition duct also provides a plurality of variable vanes at the outlet of the transition duct. The transition duct incorporates a perimeter slot (124) providing cooling to the duct outer wall and attached components. The variable vanes (120) are installed to vector the exhaust gases. This allows the aircraft to decelerate, hover or accelerate in the forward direction by commanding the position of the variable vanes. One potential application of the tip turbine engine is for vertical installations in aircraft.

Claims

1. A turbine engine assembly comprising:

a fan including a plurality of fan blades, wherein at least one of the plurality of fan blades defines a centrifugal compressor chamber therein for compressing core airflow therein and guiding the compressed core airflow toward the combustor;

a combustor burning fuel to generate a high-energy gas stream;

a turbine downstream from the combustor, the turbine rotatably drivable by the high-energy gas stream;

a transition duct downstream from the turbine and the fan, the transition duct having a first side and a second side opposite the first side; and

a plurality of variable vanes spaced across the transition duct between the sides for vectoring airflow from the fan and the combustor, wherein each of the plurality of variable vanes is pivoted at an angle, and the angles progressively increase across the transition duct between the first side and the second side.

2. The assembly claim 1 wherein the fan draws bypass air through a bypass air flow path, the assembly further including an axial compressor radially inward of the bypass air flow path.

3. The assembly of claim 1 wherein an interior of the transition duct transitions from a generally round cross-section to a generally rectangular cross-section.

4. The assembly of claim 1 wherein the first side corresponds to a desired direction of travel, and the angles progressively increase from the first side to the second side.

5. The assembly of claim 1 further including an actuator for pivoting the variable vanes about axes generally perpendicular to the air flow through the transition duct.

6. An aircraft including the turbine assembly of claim 1, wherein the fan is rotatable about a generally vertical axis that is perpendicular to a longitudinal axis of an aircraft.

7. The assembly of claim 1 wherein the plurality of vanes are each pivotable about an axis generally transverse to air flow through the engine.

13. The assembly of claim 1 wherein the plurality of vanes are each pivotable about an axis generally transverse to air flow through the engine.

8. A turbine engine and controller comprising:

a bypass fan including a plurality of fan blades, at least one of the fan blades defining a centrifugal compressor chamber therein for centrifugally compressing core airflow;

a combustor burning fuel mixed with the compressed core airflow from the centrifugal compressor chamber to generate a high-energy gas stream;

a turbine downstream from the combustor, the turbine rotatably driven by the high-energy gas stream, the turbine rotatably driving the bypass fan;

a transition duct downstream from at least one of the turbine and the fan, the transition duct transitioning air flow through the transition duct from a generally round cross-section to a generally rectangular cross-section;

a transition duct downstream from the turbine and the fan, the transition duct having a first side and a second side opposite the first side; and

a plurality of variable vanes spaced across the transition duct between the sides for vectoring airflow from the fan and the combustor, wherein each of the plurality of variable vanes is pivoted at an angle, and the angles progressively increase across the transition duct between the first side and the second side.

9. The assembly claim 8 wherein the fan draws bypass air through a bypass air flow path, the assembly further including an axial compressor radially inward of the bypass air flow path, the axial compressor compressing core airflow prior to the centrifugal compressor chamber.

10. The assembly of claim 8 wherein first side corresponds to a desired direction of travel, and the angles progressively increase from the first side to the second side.

11. The assembly of claim 8 further including an actuator for pivoting the variable vanes about axes generally perpendicular to the air flow through the transition duct.

12. An aircraft including the turbine assembly of claim 8, wherein the fan is rotatable about a generally vertical axis that is perpendicular to a longitudinal axis of an aircraft.

14. A turbine engine comprising:

a transition duct mounted proximate an outlet of the turbine engine having an outer wall defining an interior between an inlet and an outlet;

a plurality of variable vanes pivotably mounted to the outer wall proximate the outlet for vectoring airflow through the interior;

a vent through the outer wall between the inlet and the plurality of variable vanes, the vent extending entirely about an outer perimeter of the outer wall; and

wherein the turbine engine includes a fan having a plurality of fan blades including at least one hollow fan blade having a core airflow compressor chamber defined therein.

15. The transition duct of claim 14 wherein the outer wall has a generally round cross-section proximate the inlet and a generally rectangular cross-section proximate the outlet.