Mid-section of a can-annular gas turbine engine with a radial air flow discharged from the compressor section

Patent metadata

Field	Value
Publication number	US-9476355-B2
Application number	US-201213408147-A
Country	US
Kind code	B2
Filing date	Feb 29, 2012
Priority date	Feb 29, 2012
Publication date	Oct 25, 2016
Grant date	Oct 25, 2016

Abstract

A midframe portion ( 213 ) of a gas turbine engine ( 210 ) is presented, and includes a compressor section ( 212 ) configured to discharge an air flow ( 211 ) directed in a radial direction from an outlet of the compressor section ( 212 ). Additionally, the midframe portion ( 213 ) includes a manifold ( 214 ) to directly couple the air flow ( 211 ) from the compressor section ( 212 ) outlet to an inlet of a respective combustor head ( 218 ) of the midframe portion ( 213 ).

First claim

The invention claimed is:

1. A midframe portion of a gas turbine engine, comprising:
a compressor section comprising a last stage blade with a leading edge aligned with a leading edge of blades positioned upstream of the last stage blade, said last stage blade configured to discharge an air flow directed in a radial direction from an outlet of the compressor section;
a plurality of discrete combustor heads circumferentially arranged around a rotor assembly of the gas turbine engine in an annular configuration; and
a plurality of manifolds circumferentially arranged around the rotor assembly, wherein each manifold is configured to directly couple a respective portion of the air flow discharged from the compressor section to a respective combustor head;
wherein the compressor section, the plurality of discrete combustor heads and the plurality of manifolds are positioned within a single casing to form a chamber;
wherein an air flow is directed from an intermediate stage of the compressor section into the chamber to circulate stagnant air within the chamber.

2. The midframe portion of claim 1 , wherein the last stage blade is configured to receive the air flow directed in a longitudinal direction at the leading edge and configured to discharge the air flow in the radial direction at a trailing edge.

3. The midframe portion of claim 2 , wherein a sweep angle of the trailing edge is selected to form a desired tangential velocity component of the air flow at the outlet of the compressor section; and wherein the air flow is discharged in a mixed radial-tangential direction from the outlet of the compressor section, said mixed radial-tangential direction based on the sweep angle.

4. The midframe portion of claim 3 , wherein the sweep angle is measured in the tangential direction with respect to the radial direction and wherein the sweep angle is greater than zero degrees.

5. The midframe portion of claim 3 , wherein the sweep angle of the trailing edge is selected such that the mixed radial-tangential direction of the air flow discharged from the compressor section outlet is aligned with an inlet of a diffuser.

6. The midframe portion of claim 3 , wherein each respective manifold is configured to receive a portion of the air flow from the compressor section; wherein the sweep angle of the trailing edge is selected such that the tangential velocity component of the air flow entering the respective manifold is selected, such that the manifold is configured to turn the air flow from the mixed radial-tangential direction to a direction oriented at an offset angle in the tangential direction with respect to the longitudinal direction.

7. The midframe portion of claim 6 , wherein the offset angle is 70 degrees.

8. The midframe portion of claim 6 , wherein said manifold is configured such that the offset angle in the tangential direction with respect to the longitudinal direction corresponds to a predetermined tangential angle with respect to the longitudinal direction at which a first stage blade of a turbine downstream of the combustor head is configured to receive air flow.

9. The midframe portion of claim 6 , further comprising a plurality of transitions positioned downstream of the plurality of combustor heads, wherein the respective manifold and a respective transition are both aligned along the direction oriented at the offset angle in the tangential direction with respect to the longitudinal direction.

10. The midframe portion of claim 3 , wherein said manifold is configured to rotate a direction of the air flow from the mixed radial-tangential direction at the inlet of the manifold to a direction oriented at an offset angle in the tangential direction with respect to the longitudinal direction at the inlet to the respective combustor head.

11. The midframe portion of claim 1 , wherein an outer diameter of an outlet of each manifold coupled to the respective combustor head inlet is greater than an outer diameter of the combustor head inlet.

12. The midframe portion of claim 11 , wherein a face of each manifold outlet is parallel with a face of the respective combustor head inlet, to align the air flow from each manifold into the respective combustor head inlet.

13. The midframe portion of claim 1 , wherein the compressor section and manifolds are configured such that the air flow is rotated by a total angle of less than 180 degrees in a longitudinal-radial plane of the gas turbine engine between the compressor section and the respective combustor head.

14. A midframe portion of a gas turbine engine, comprising:
a compressor section comprising a last stage blade with a leading edge aligned with a leading edge of blades positioned upstream of the last stage blade, said last stage blade configured to discharge an air flow directed in a mixed radial-tangential direction from an outlet of the compressor section; and
a manifold to directly couple the air flow from the compressor section outlet to an inlet of a respective combustor head of the midframe portion;
wherein the manifold is oriented at an angular offset in the tangential direction with respect to a longitudinal direction, such that the manifold is configured to initiate a longitudinal turn in the air flow from the mixed radial-tangential direction to a direction oriented at the angular offset in the tangential direction with respect to the longitudinal direction;
wherein a plurality of manifolds, a plurality of combustor heads and a plurality of transitions positioned downstream of the combustor heads are positioned within a single casing, to form a chamber;
wherein an air flow is directed from an intermediate stage of the compressor section into the chamber to circulate stagnant air within the chamber.

15. The midframe portion of claim 14 , wherein a pressure of air flow from the intermediate stage is an intermediate pressure, said intermediate pressure being less than a static pressure of the air flow in the manifold, to establish a controlled leakage of air flow across an interface between an outlet of the manifold and the combustor head inlet, to disperse stagnant air within the interface.

Assignees

• Little David A
• Mcquiggan Gerard
• Wasdell David L
• Siemens Energy Inc

Inventors

• Little David A
• Mcquiggan Gerard
• Wasdell David L

Classifications

• F02C3/14 Primary

  characterised by the arrangement of the combustion chamber in the plant (combustion chambers per se F23R; F02C3/205 takes precedence) · CPC title