Offtakes for gas turbine engine secondary gas flows

Patent metadata

Field	Value
Publication number	US-10612416-B2
Application number	US-201514846874-A
Country	US
Kind code	B2
Filing date	Sep 7, 2015
Priority date	Sep 5, 2014
Publication date	Apr 7, 2020
Grant date	Apr 7, 2020

Abstract

A turbo machinery case includes a shell body extending circumferentially about a longitudinal axis and defining therein a main gas path. The shell body defines a first offtake opening and a second offtake opening that extend in a circumferential direction about the longitudinal axis. The first and second offtake openings are defined at a common axial location with respect to the longitudinal axis of the turbo machinery case.

First claim

What is claimed is:

1. A turbo machinery case, comprising:
a shell body extending circumferentially about a longitudinal axis, the shell body defining a main gas path therethrough with a first offtake opening and a second offtake opening circumferentially spaced from the first offtake opening, the first and second offtake openings having a common axial position;
wherein the shell body defines a first internal plenum in fluid communication with the main gas path through the first offtake opening, and the case further comprises a second internal plenum in fluid communication with the main gas path though the second offtake opening;
wherein the shell body includes:
an outer shell;
an inner shell radially inward of the outer shell; and
an intermediate shell disposed between the inner shell and the outer shell, wherein an inner surface of the outer shell and an outer surface of the intermediate shell bound the first internal plenum, and
a ligament connecting the inner shell to the intermediate shell, wherein opposite faces of the ligament bound the first offtake opening and the second offtake opening.

2. A case as recited in claim 1 , wherein the first offtake opening is offset circumferentially from the second offtake opening.

3. A case as recited in claim 1 , wherein the first offtake opening and the second offtake opening are both offset from the longitudinal axis by a common radial distance.

4. A case as recited in claim 1 , wherein the first plenum is arranged radially outward of the second plenum.

5. A case as recited in claim 1 , wherein the first offtake opening extends radially outward from the main gas path to the first internal plenum.

6. A case as recited in claim 1 , wherein an outer surface of the inner shell and inner surface of the intermediate shell bound the second offtake opening.

7. A case as recited in claim 6 , wherein the second offtake opening extends radially outward and axially aft between the main gas path and the second plenum.

8. A case as recited in claim 1 , wherein the first offtake opening is one of a plurality of first offtake openings and the second offtake opening is one of a second plurality of offtake openings, each of the first offtake openings being circumferentially interspersed between the second offtake openings.

9. A compressor module, comprising:
a turbo machinery case, including:
a shell body extending circumferentially about a longitudinal axis, the shell body defining a main gas path therethrough with a first offtake opening and a second offtake opening defined in the shell body and spaced in a circumferential direction, and the second offtake opening at a common axial position with the first offtake opening;
wherein the shell body defines a first internal plenum in fluid communication with the main gas path through the first offtake opening, and the case further comprises a second internal plenum in fluid communication with the main gas path though the second offtake opening;
wherein the shell body includes:
an outer shell;
an inner shell radially inward of the outer shell; and
an intermediate shell disposed between the inner shell and the outer shell, wherein an inner surface of the outer shell and an outer surface of the intermediate shell bound the first internal plenum, and
a ligament connecting the inner shell to the intermediate shell, wherein opposite faces of the ligament bound the first offtake opening and the second offtake opening; and
a rotor stage outer air seal seated within the shell body disposed axially aft of the first and second offtake openings.

10. A compressor module as recited in claim 9 , wherein the first offtake opening is one of a plurality of first offtake openings and the second offtake opening is one of a second plurality of offtake openings, each of the first offtake openings being circumferentially interspersed between the second offtake openings.

11. A gas turbine engine, comprising:
a turbine module; and
a compressor module operatively associated with the turbine module, including:
a shell body extending circumferentially about a longitudinal axis, the shell body defining a main gas path therethrough with a first offtake opening and a second offtake opening defined in the shell body in a circumferential direction, and the second offtake opening at a common axial position with the first offtake opening, wherein a bleed port defined in the shell body is in fluid communication with the main gas path through the first offtake opening, and wherein a cooling channel defined within the turbine module is in fluid communication with the main gas path through the second offtake opening; and
wherein the shell body defines a first internal plenum in fluid communication with the main gas path through the first offtake opening, and the case further comprises a second internal plenum in fluid communication with the main gas path though the second offtake opening;
wherein the shell body includes:
an outer shell;
an inner shell radially inward of the outer shell; and
an intermediate shell disposed between the inner shell and the outer shell, wherein an inner surface of the outer shell and an outer surface of the intermediate shell bound the first internal plenum, and
a ligament connecting the inner shell to the intermediate shell, wherein opposite faces of the ligament bound the first offtake opening and the second offtake opening.

Assignees

• Pratt & Whitney
• United Technologies Corp

Inventors

• Hatfield Jason

Classifications

• F02C9/18

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F01D25/24 Primary

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F04D27/0215

  Arrangements therefor, e.g. bleed or by-pass valves · CPC title

• F01D25/26 Primary

  Double casings; Measures against temperature strain in casings · CPC title

• F02C6/08

  the gas being bled from the gas-turbine compressor · CPC title