Inter-turbine ducts with variable area ratios

Patent metadata

Field	Value
Publication number	US-9534497-B2
Application number	US-201213462738-A
Country	US
Kind code	B2
Filing date	May 2, 2012
Priority date	May 2, 2012
Publication date	Jan 3, 2017
Grant date	Jan 3, 2017

Abstract

A turbine section of a gas turbine engine is annular about a longitudinal axis. The turbine section includes a first turbine with a first inlet and a first outlet; a second turbine with a second inlet and a second outlet; and an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine. The inter-turbine duct has a first station with a first meridional area, a second station with a second meridional area, and a third station with a third meridional area. The first station is upstream of the second station and the second station is upstream of the third station, and the second meridional area is less than or equal to the first meridional area.

First claim

What is claimed is:

1. A turbine section of a gas turbine engine, the turbine section being annular about a longitudinal axis, the turbine section comprising:
a first turbine with a first inlet and a first outlet;
a second turbine with a second inlet and a second outlet; and
an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct having a first station with a first meridional area, a second station with a second meridional area, and a third station with a third meridional area, wherein the first station is upstream of the second station and the second station is upstream of the third station, and wherein the second meridional area is less than or equal to the first meridional area.

2. The turbine section of claim 1 , wherein the third area meridional ratio is greater than the first meridional area ratio and the second meridional area ratio.

3. The turbine section of claim 1 , wherein the first meridional area is calculated according to the following Equation:
A M =2π* R M *h M

where
A M is the first meridional area;
R M is a radius of the duct at the first station; and
h M is a meridional height at the first station.

4. The turbine section of claim 3 , wherein the meridional height (h M ) is calculated according to the following Equation:
h M =h S *cos(Φ M −Φ S )

where
h M is the meridional height at the first station;
h S is a station height;
Φ M is a meridional angle; and
Φ S is a station angle.

5. The turbine section of claim 1 , wherein the second meridional area is less that the first meridional area.

6. The turbine section of claim 5 , wherein the inter-turbine duct has a first portion extending between the first station and the second station, wherein the first portion has a continuously converging meridional area distribution in the downstream direction.

7. The turbine section of claim 1 , wherein the first meridional area is equal to the second meridional area.

8. The turbine section of claim 7 , wherein the inter-turbine duct has a first portion extending between the first station and the second station, wherein the first portion has a continuously constant meridional area distribution in the downstream direction.

9. The turbine section of claim 1 , wherein the inter-turbine duct has a first portion extending between the first station and the second station and a second portion extending between the second station and the third station, wherein the second portion has an continuously diverging meridional area distribution.

10. The turbine section of claim 1 , wherein the first station is defined at an inlet of the inter-turbine duct.

11. The turbine section of claim 10 , wherein the third station is defined at an outlet of the inter-turbine duct.

12. The turbine section of claim 1 , wherein the inter-turbine duct has an axial length and a first portion extending between the first station and the second station, and wherein the first portion extends to about 15%-80% of the axial length.

13. The turbine section of claim 1 , wherein the first turbine is a high pressure turbine and the second turbine is a low pressure turbine.

14. An inter-turbine duct extending between a first turbine having a first radial diameter and a second turbine having a second radial diameter, the first radial diameter being less than the second radial diameter, the inter-turbine duct comprising:
a hub; and
a shroud circumscribing the hub to form a flow path fluidly coupled to the first turbine and the second turbine, wherein the hub and shroud converge or maintain a constant separation with respect to meridional area in a first portion and the hub and shroud diverge relative to one another in a second portion with respect to meridional area.

15. The inter-turbine duct of claim 14 , wherein first portion is upstream of the second portion.

16. The inter-turbine duct of claim 14 , wherein the first portion is continuously constant with respect to meridional area.

17. The inter-turbine duct of claim 14 , wherein the first portion is continuously converging with respect to meridional area.

18. The inter-turbine duct of claim 14 , wherein the second portion is continuously diverging.

19. The inter-turbine duct of claim 14 , wherein the inter-turbine duct has an axial length, and wherein the first portion extends to about 15%-80% of the axial length.

20. A turbine section of a gas turbine engine, the turbine section being annular about a longitudinal axis, the turbine section comprising:
a high pressure turbine with a first inlet and a first outlet;
a low pressure turbine with a second inlet and a second outlet; and
an inter-turbine duct extending from the first outlet to the second inlet and configured to direct an air flow from the first turbine to the second turbine, the inter-turbine duct having a first station with a first meridional area ratio, a second station with a second meridional area ratio, and a third station with a third meridional area ratio, wherein the first station is upstream of the second station and the second station is upstream of the third station, and wherein the second meridional area ratio is less than or equal to the first meridional area ratio,
wherein the inter-turbine duct has an axial length and a first portion extending between the first station and the second station, and wherein the first portion extends to about 15%-80% of the axial length, and
wherein the first meridional area is calculated according to the following Equation:
A M =2π* R M *h M

where
A M is the first meridional area;
R M is a radius of the duct at the first station;
h M is a meridional height at the first station; and
wherein a meridional angle of the meridional height is determined by taking an average of a shroud angle (Φ SHROUD ) and a hub angle (Φ HUB ) at axial endpoints of the respective station.

Assignees

• Kuchana Vinayender
• Srinivasan Balamurugan
• Guntu Sujatha
• Malak Malak Fouad
• Couey Paul
• Mckeever Craig
• Honeywell Int Inc

Inventors

• Kuchana Vinayender
• Srinivasan Balamurugan
• Guntu Sujatha
• Malak Malak Fouad
• Couey Paul
• Mckeever Craig

Classifications

• F01D5/145 Primary

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• F01D9/041

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

• Y02T50/671

  Cross-Sectional Technologies · mapped topic

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title