Virtual multi-stream gas turbine engine

Patent metadata

Field	Value
Publication number	US-9957823-B2
Application number	US-201514604228-A
Country	US
Kind code	B2
Filing date	Jan 23, 2015
Priority date	Jan 24, 2014
Publication date	May 1, 2018
Grant date	May 1, 2018

Abstract

A gas turbine engine is provided that includes a core flow path to direct a core stream flow. A common flow path is outboard of the core flow path, where the common flow path directs both a second stream flow and a third stream flow. Another gas turbine engine is provided that includes an outer case structure around a central longitudinal engine axis. An intermediate case structure is inboard of the outer case structure, where the intermediate case structure and the outer case structure direct both a third stream flow and a second stream flow. An inner case structure is inboard of the intermediate case structure, where the inner case structure and the intermediate case structure direct a core stream flow.

First claim

What is claimed:

1. A gas turbine engine, comprising:
a fan section;
a core flow path to direct a core stream flow;
a common flow path outboard of the core flow path, the common flow path to direct both a second stream flow and a third stream flow, the common flow path at least partially formed between an outer case structure and a case structure; and
a vane array with a multiple of span adaptive stators operable to separately control the second stream flow and the third stream flow,
wherein the fan section is immediately upstream of the case structure wherein the case structure separates the common flow path from the core flow path, and
wherein the multiple of span adaptive stators are upstream of the common flow path.

2. The gas turbine engine as recited in claim 1 , wherein the third stream flow and the second stream flow each operate at a different total temperature, total pressure, and relative velocity, and equivalent static pressure.

3. The gas turbine engine as recited in claim 1 , wherein the third stream flow and the second stream flow each operate at equivalent static pressure.

4. The gas turbine engine as recited in claim 1 , wherein the third stream flow and the second stream flow each operate at a different relative swirl.

5. The gas turbine engine as recited in claim 1 , where each span adaptive stator of the multiple of span adaptive stators includes a first spanwise segment and a second spanwise segment each individually rotatable about an axis.

6. The gas turbine engine as recited in claim 1 , where each span adaptive stator of the multiple of span adaptive stators includes a first spanwise segment and a second spanwise segment each with a trailing edge flap rotatable about an axis.

7. The gas turbine engine as recited in claim 1 , where each span adaptive stator of the multiple of span adaptive stators includes a first spanwise segment and a second spanwise segment each with a leading edge flap rotatable about an axis.

8. The gas turbine engine as recited in claim 1 , where each span adaptive stator of the multiple of span adaptive stators includes a first spanwise segment and a second spanwise segment each with a leading edge flap rotatable about an axis and a trailing edge flap rotatable about an axis.

9. The gas turbine engine as recited in claim 1 , where each span adaptive stator of the multiple of span adaptive stators includes a circumferential partial span shroud to at least partially define co-annular passageways between the second stream flow and the third stream flow.

10. The gas turbine engine as recited in claim 9 , further comprising a rotor disk with a multiple of rotor blades, each rotor blade of the multiple of rotor blades including a circumferential partial span blade shroud radially aligned with the circumferential partial span shroud.

11. A gas turbine engine, comprising:
a fan section;
an outer case structure around a central longitudinal engine axis;
an intermediate case structure inboard of the outer case structure, the intermediate case structure and the outer case structure to direct a second stream flow and a third stream flow, respectively;
an inner case structure inboard of the intermediate case structure, the inner case structure and the intermediate case structure to direct a core stream flow; and
a vane array with a multiple of span adaptive stators operable to separately control the second stream flow and the third stream flow,
wherein the fan section is immediately upstream of the intermediate case structure,
wherein the intermediate case structure separates the core stream flow from the second stream flow, and
wherein the multiple of span adaptive stators are upstream of a common flow path at least partially formed between the outer case structure and the intermediate case structure, the common flow path to receive both the third stream flow and the second stream flow.

12. The gas turbine engine as recited in claim 11 , wherein the inner case structure and the intermediate case structure at least partially form a core flow path inboard of the common flow path, the core flow path to receive the core stream flow.

13. A method of operating a gas turbine engine, comprising:
directing both a third stream flow and a second stream flow from a fan section into a common flow path that is radially outboard of a core flow path; and
separately controlling the second stream flow and the third stream flow using a vane array with a multiple of span adaptive stators,
wherein the fan section is immediately upstream of a case structure that separates the common flow path from the core flow path,
wherein the multiple of span adaptive stators are upstream of the common flow path, and
wherein the common flow path is at least partially formed between an outer case structure and the case structure.

14. The method as recited in claim 13 , further comprising at least partially segregating the third stream flow and the second stream flow with a circumferential partial span shroud that extends from the multiple of span adaptive stators.

15. The method as recited in claim 14 , further comprising at least partially segregating the third stream flow and the second stream flow with a circumferential partial span blade shroud that extends from each rotor blade of a multiple of rotor blades upstream of the circumferential partial span shroud, the circumferential partial span blade shroud radially aligned with the circumferential partial span shroud.

16. The method as recited in claim 13 , further comprising at least partially forming the third stream flow and the second stream flow by morphing at least one span adaptive stator of the multiple of span adaptive stators.

17. The method as recited in claim 13 , wherein the third stream flow and the second stream flow operate at a different total temperature, total pressure, and relative velocity, and an equivalent static pressure.

Assignees

• United Technologies Corp

Inventors

• Epstein Alan H

Classifications

• F01D17/162

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• F01D5/148

  Blades with variable camber, e.g. by ejection of fluid · CPC title

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F01D1/023

  the working-fluid being divided into several separate flows (F01D3/02 takes precedence); several separate fluid flows being united in a single flow; the machine or engine having provision for two or more different possible fluid flow paths · CPC title