# US 11,078,842 B2 · Exhaust distribution manifold

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- Number: US 11,078,842 B2
- Document ID: US11078842B2
- Status: Granted
- Kind: B2
- Application number: 16/365,235
- Filed: 2019-03-26
- Published: 2020-10-01
- Granted: 2021-08-03
- Earliest claimed: 2019-03-26
- Assignees: Raytheon Technologies Corporation
- Applicants: United Technologies Corporation
- Inventors: Michael R. Thomas
- Web page: https://patentgrep.com/patent/US11078842B2

## CPC

- F02C 7/141: of working fluid
- F02C 7/185: {Cooling means for reducing the temperature of the cooling air or gas}
- F02C 7/18: the medium being gaseous, e.g. air {(F02C7/125 takes precedence)}
- F02K 3/115: by means of indirect heat exchange
- F28F 9/0246: {Arrangements for connecting header boxes with flow lines}
- F28F 9/026: {with static flow control means, e.g. with means for uniformly distributing heat exchange media into conduits}
- F05D 2220/32: in gas turbines
- F05D 2260/201: by impingement of a fluid
- F05D 2260/213: by the provision of a heat exchanger within the cooling circuit
- F28F 9/0265: {by using guiding means or impingement means inside the header box}
- F28F 9/0273: {with multiple holes}
- F28F 9/028: {by using inserts for modifying the pattern of flow inside the header box, e.g. by using flow restrictors or permeable bodies or blocks with channels}
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00)
- F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00)
- F28F: DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION (water and air traps, air venting F16)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A cooling system for a gas turbine engine may comprise a heat exchanger configured to receive a cooling airflow. The heat exchanger may receive the cooling flow at a cooling flow input of the heat exchanger and output the cooling airflow at an exhaust output of the heat exchanger. An exhaust distribution manifold may be fluidly coupled to the exhaust output of the heat exchanger. The exhaust distribution manifold may define a plurality of openings.

## Claims

### Claim 1

A cooling system for a gas turbine engine, comprising:
a heat exchanger configured to receive a cooling airflow, wherein the heat exchanger is configured to receive the cooling airflow at a cooling flow input of the heat exchanger, and wherein the heat exchanger is configured to output the cooling airflow at a first exhaust output of the heat exchanger;
a first exhaust distribution manifold fluidly coupled to the first exhaust output of the heat exchanger, wherein the first exhaust distribution manifold defines a plurality of first openings; and
a second exhaust distribution manifold fluidly coupled to a second exhaust output of the heat exchanger, wherein the second exhaust distribution manifold defines a plurality of second openings.

### Claim 2 (depends on 1)

The cooling system of claim 1, further comprising:
an inlet conduit coupled to an inlet of the heat exchanger; and
a return conduit coupled to an outlet of the heat exchanger.

### Claim 3 (depends on 2)

The cooling system of claim 2, wherein a first end of the first exhaust distribution manifold has a first diameter and a second end of the first exhaust distribution manifold located opposite the first end has a second diameter less than the first diameter.

### Claim 4 (depends on 3)

The cooling system of claim 3, wherein the plurality of first openings are formed over approximately 100° of a circumference of the first exhaust distribution manifold.

### Claim 5 (depends on 3)

The cooling system of claim 3, wherein the plurality of first openings comprises a first pair of adjacent openings proximate the first end of the first exhaust distribution manifold and a second pair of adjacent openings proximate the second end of the first exhaust distribution manifold, and wherein a pitch of the first pair of adjacent openings is greater than a pitch of the second pair of adjacent openings.

### Claim 6 (depends on 1)

The cooling system of claim 1, wherein the plurality of first openings and the plurality of second openings are oriented in a generally aft direction.

### Claim 7 (depends on 1)

The cooling system of claim 1, wherein a surface area of a first opening of the plurality of first openings is greater than a surface area of a second opening of the plurality of first openings.

### Claim 8

A gas turbine engine, comprising:
an inner engine case structure;
an outer engine case structure radially outward of the inner engine case structure; and
a cooling system located at least partially between the inner engine case structure and the outer engine case structure, the cooling system comprising:
a first heat exchanger configured to receive a cooling airflow; and
a first exhaust distribution manifold fluidly coupled to a first exhaust output of the first heat exchanger, wherein the first exhaust distribution manifold defines a plurality of first openings, and wherein a distal end of the first exhaust distribution manifold is circumferentially offset from an inlet end of the first exhaust distribution manifold.

### Claim 9 (depends on 8)

The gas turbine engine of claim 8, wherein the cooling system further comprises:
an inlet conduit coupled to an inlet of the first heat exchanger; and
a return conduit coupled to an outlet of the first heat exchanger.

### Claim 10 (depends on 8)

The gas turbine engine of claim 8, wherein the plurality of first openings are formed over approximately 100° of a circumference of the first exhaust distribution manifold.

### Claim 11 (depends on 10)

The gas turbine engine of claim 10, wherein the inlet end of the first exhaust distribution manifold has a first diameter and the distal end of the first exhaust distribution manifold has a second diameter less than the first diameter.

### Claim 12 (depends on 11)

The gas turbine engine of claim 11, wherein a pitch of the plurality of first openings decreases in a direction extending from the inlet end of the first exhaust distribution manifold to the distal end of the first exhaust distribution manifold.

### Claim 13 (depends on 8)

The gas turbine engine of claim 8, wherein a shape of a first opening of the plurality of first openings is different from a shape of a second opening of the plurality of first openings.

### Claim 14 (depends on 8)

The gas turbine engine of claim 8, wherein a surface area of a first opening of the plurality of first openings is greater than a surface area of a second opening of the plurality of first openings, and wherein the first opening is located closer to the inlet end of the first exhaust distribution manifold as compared to the second opening.

### Claim 15 (depends on 8)

The gas turbine engine of claim 8, wherein the cooling system further comprises
a second heat exchanger configured to receive the cooling airflow; and
a second exhaust distribution manifold fluidly coupled to a second exhaust output of the second heat exchanger, wherein the second exhaust distribution manifold defines a plurality of second openings.

### Claim 16 (depends on 8)

The gas turbine engine of claim 8, wherein the cooling system further comprises a second exhaust distribution manifold fluidly coupled to a second exhaust output of the first heat exchanger, wherein the second exhaust distribution manifold defines a plurality of second openings.

### Claim 17

An exhaust distribution manifold configured to be fluidly coupled to an exhaust output of a heat exchanger, the exhaust distribution manifold comprising:
a first end defining an inlet of the exhaust distribution manifold and having a first diameter;
a second end located opposite the first end and have a second diameter less than the first diameter, wherein the second end is circumferentially offset from the first end; and
a plurality of openings formed between the first end and the second end, wherein the plurality of openings are formed over approximately 100° of a circumference of the exhaust distribution manifold, and wherein approximately 260° of the circumference of the exhaust distribution manifold is devoid of openings.

### Claim 18 (depends on 17)

The exhaust distribution manifold of claim 17, wherein a surface area of a first opening of the plurality of openings is greater than a surface area of a second opening of the plurality of openings.

### Claim 19 (depends on 18)

The exhaust distribution manifold of claim 18, wherein the first opening is formed closer to the first end of the exhaust distribution manifold as compared to the second opening.