# US 8,783,412 B2 · Sound absorber for a gas turbine exhaust cone, and method for the production thereof

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- Number: US 8,783,412 B2
- Document ID: US8783412B2
- Status: Granted
- Kind: B2
- Application number: 13/980,018
- Filed: 2012-01-19
- Published: 2013-11-21
- Granted: 2014-07-22
- Earliest claimed: 2011-01-19
- Assignees: Rolls-Royce Deutschland Ltd & Co KG
- Applicants: Predrag Todorovic
- Inventors: Predrag Todorovic
- Web page: https://patentgrep.com/patent/US8783412B2

## CPC

- F01N 13/00: Exhaust or silencing apparatus characterised by constructional features
- F01D 25/30: Exhaust heads, chambers, or the like
- F02C 7/045: having provisions for noise suppression
- F02C 7/24: Heat or noise insulation (air intakes having provisions for noise suppression F02C7/045; turbine exhaust heads, chambers, or the like F01D25/30; silencing nozzles of jet-propulsion plants F02K1/00)
- F02K 1/44: Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction (F02K1/40 takes precedence)
- F02K 1/827: {Sound absorbing structures or liners}
- F05D 2250/283: honeycomb
- F05D 2260/96: Preventing, counteracting or reducing vibration or noise
- Y10T 29/4957: Sound device making
- F01N: GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL-COMBUSTION ENGINES (arrangements in connection with gas exhaust of propulsion units in vehicles B60K13/00; combustion-air intake silencers specially adapted for, or arranged on, internal-combustion engines F02M35/00; protecting against, or damping, noise in general G10K11/16)
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- 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)
- F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A method for manufacturing a sound absorber, the outer wall of which is provided with a plurality of recesses, with funnel-like cone elements each being assigned to the recesses inside the sound absorber, said cone elements having a larger opening facing radially outwards and a smaller opening facing radially inwards, with adjacent cone elements each being provided on a strip-shaped first carrier band, with cup elements being provided radially on the inside relative to the cone elements, and each cup element receiving one cone element, with adjacent cup elements each being provided on a strip-shaped first carrier band, with the first carrier bands being arranged adjacently in a first direction, and the second carrier bands being arranged adjacently in a second direction, with the directions crossing each other and the carrier bands being joined to one another and to the outer wall to form a rigid body.

## Claims

### Claim 1

A method for manufacturing a sound absorber,
providing an outer wall for the sound absorber having a plurality of through passages;
providing a plurality of funnel-like cone elements each being assigned to certain of the plurality of through passages inside the sound absorber, the cone elements having a larger opening facing radially outwards and a smaller opening facing radially inwards, with a quantity of the cone elements being provided adjacent to one another longitudinally along each of a plurality of strip-shaped first carrier bands;
providing a plurality of cup elements on a radially interior side of the cone elements, with each cup element receiving only one cone element, and with a quantity of the cup elements being provided adjacent to one another longitudinally along each of a plurality of strip-shaped second carrier bands;
arranging the plurality of the first carrier bands side-by-side to one another and skewed in a first direction with respect to an axis of the sound absorber;
arranging the plurality of the second carrier bands side-by-side to one another and skewed in a second direction with respect to the axis of the sound absorber, with the first and second directions crossing each other such that each first carrier band crosses a plurality of second carrier bands and each second carrier band crosses a plurality of first carrier bands;
joining the carrier bands to one another and to the outer wall in order to form a rigid body.

### Claim 2 (depends on 1)

The method of claim 1, and further comprising manufacturing at least one chosen from the cone elements and the cup elements by forming the at least one chosen from the cone elements and the cup elements integrally with the respective carrier band.

### Claim 3

A gas-turbine exhaust cone, comprising:
an outer wall including a plurality of through passages;
a plurality of funnel-like cone elements each being assigned to certain of the plurality of through passages inside the gas-turbine exhaust cone, the cone elements each having a larger opening facing radially outwards and a smaller opening facing radially inwards,
a plurality of strip-shaped first carrier bands, each of which has a longitudinal extension and on each of which a quantity of the cone elements are provided adjacent to one another along the longitudinal extension;
a plurality of cup elements being provided radially on an inside relative to the cone elements, each cup element receiving only one cone element;
a plurality of strip-shaped second carrier bands, each of which has a longitudinal extension and on each of which a quantity of the cup elements are provided adjacent to one another along the longitudinal extension;
the first carrier bands being arranged side-by-side to one another and skewed in a first direction with respect to an axis of the exhaust cone;
the second carrier bands being arranged side-by-side to one another and skewed in a second direction with respect to the axis of the exhaust cone;
the first and second directions crossing each other such that each first carrier band crosses a plurality of second carrier bands and each second carrier band crosses a plurality of first carrier bands;
the first and second carrier bands being joined to one another and to the outer wall to form a rigid body.

### Claim 4 (depends on 3)

The gas-turbine exhaust cone of claim 3, wherein at least one chosen from the cone elements and the cup elements are integrally formed with the respective carrier bands.

### Claim 5 (depends on 3)

The gas-turbine exhaust cone of claim 3, wherein the outer wall includes a plurality of through passages associated with each cone element.

### Claim 6 (depends on 3)

The gas-turbine exhaust cone of claim 3, wherein the outer wall includes double walls and a honeycomb-structured layer arranged between the double walls.

### Claim 7 (depends on 3)

The gas-turbine exhaust cone of claim 3, and further comprising stiffening elements arranged radially inside the joined second carrier bands, the stiffening elements being elongated in design and supporting the cup elements, and, being arranged between adjacent rows of cup elements.

### Claim 8 (depends on 3)

The gas-turbine exhaust cone of claim 3, wherein the cone elements and the cup elements are provided in an axial direction at partial areas along a length of the gas-turbine exhaust cone.

### Claim 9 (depends on 3)

An acoustic absorber including a gas-turbine exhaust cone in accordance with claim 3.

### Claim 10 (depends on 3)

The gas-turbine exhaust cone of claim 3, wherein at least one chosen from the cone elements and the cup elements are separate parts joined to respective carrier band provided with second through passages.

### Claim 11 (depends on 3)

The gas-turbine exhaust cone of claim 3, wherein the cone elements each have, in a radial direction, a height which is less than a depth of each of the cup elements.

### Claim 12 (depends on 3)

The gas-turbine exhaust cone of claim 3, wherein the outer wall includes a single through passage associated with each cone element.

### Claim 13 (depends on 3)

The gas-turbine exhaust cone of claim 3, wherein the cone elements and the cup elements are provided in an axial direction essentially along an entire length of the gas-turbine exhaust cone.

### Claim 14 (depends on 3)

The gas-turbine exhaust cone of claim 3, wherein the outer wall includes a flange at each end and end areas of the carrier bands are connected to adjacent flanges.

### Claim 15 (depends on 1)

The method of claim 1, and further comprising providing stiffening elements arranged radially inside the joined second carrier bands, the stiffening elements being elongated in design and supporting the cup elements, and arranging the stiffening elements between adjacent rows of cup elements.

### Claim 16 (depends on 1)

The method of claim 1, and further comprising forming the at least one chosen from the cone elements and the cup elements as separate parts and joining the at least one chosen from the cone elements and the cup elements to the respective carrier band provided with second through passages.