# US 11,028,705 B2 · Transition piece having cooling rings

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- Number: US 11,028,705 B2
- Document ID: US11028705B2
- Status: Granted
- Kind: B2
- Application number: 15/923,184
- Filed: 2018-03-16
- Published: 2019-09-19
- Granted: 2021-06-08
- Earliest claimed: 2018-03-16
- Assignees: Doosan Heavy Industries Construction Co., Ltd
- Applicants: Doosan Heavy Industries & Construction Co., Ltd.
- Inventors: Esam Abu-Irshaid; Michael Brody; Kevin James Spence
- Web page: https://patentgrep.com/patent/US11028705B2

## CPC

- F01D 9/023: {Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings}
- F23R 3/005: {Combined with pressure or heat exchangers}
- F01D 25/12: Cooling
- F23R 3/002: {Wall structures (F23R3/02 and F23R3/007 take precedence)}
- F23R 3/06: Arrangement of apertures along the flame tube
- F05D 2220/32: in gas turbines
- F05D 2240/35: Combustors or associated equipment
- F05D 2260/201: by impingement of a fluid
- F05D 2260/202: by film cooling
- F23R 2900/00014: Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
- F23R 2900/03041: Effusion cooled combustion chamber walls or domes
- F23R 2900/03042: Film cooled combustion chamber walls or domes
- F23R 2900/03044: Impingement cooled combustion chamber walls or subassemblies
- Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft
- F01D: NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES (machines or engines for liquids F03; non-positive displacement pumps F04D)
- F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16)
- 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 transition piece can include: an inner transition piece providing a gas channel; a plurality of cooling rings disposed on the inner transition piece; a plurality of film holes formed on the inner transition piece; and a plurality of impingement holes formed on the plurality of cooling rings, wherein the plurality of film holes are arranged to correspond to the plurality of cooling rings. Each of the plurality of cooling rings includes a cavity such that the plurality of film holes connect the cavity to the gas channel and the plurality of impingement holes connect the cavity to an outside of the inner transition piece.

## Claims

### Claim 1

A transition piece having a first end configured to be coupled to a turbine and a second end disposed opposite to the first end and configured to be coupled to a combustor, the transition piece comprising:
an inner transition piece providing a gas channel, the inner transition piece including
an inner surface facing the gas channel, and
an outer surface disposed opposite to the inner surface so as to face an outside of the inner transition piece, the outside of the inner transition piece configured to receive a flow of cooling air in an axial direction of the transition piece, the cooling air flowing over the transition piece from the first end to the second end;
a plurality of cooling rings disposed on the outer surface of the inner transition piece and separated from each other in the axial direction, each cooling ring of the plurality of cooling rings including a three-sided structure configured with the outer surface to form a continuous cavity having an annular shape surrounding the inner transition piece, the three-sided structure including two axially facing sides respectively connected to the outer surface of the inner transition piece, and an outwardly disposed side connecting the two axially facing sides, the two axially facing sides substantially parallel to each other such that each of the two axially facing sides is substantially perpendicular to the outer surface of the inner transition piece, the outwardly disposed side facing the outside of the inner transition piece in a radial direction and receiving the flow of cooling air in the axial direction of the transition piece;
a plurality of cooling rings disposed on the outer surface of the inner transition piece and separated from each other in the axial direction, each cooling ring of the plurality of cooling rings including a three-sided structure configured with the outer surface to form a continuous cavity having an annular shape surrounding the inner transition piece, the three-sided structure including the flow of cooling air in the axial direction of the transition piece;
a plurality of film holes formed through the inner transition piece and configured to enable the continuous cavity of each of the plurality of cooling rings to communicate with the gas channel; and
a plurality of impingement holes formed through the outwardly disposed side of the cooling ring and configured to enable the continuous cavity of each of the plurality of cooling rings to communicate with the outside of the inner transition piece,
wherein the outwardly disposed side of each cooling ring of the plurality of cooling rings receives a portion of a downstream flow of the cooling air from the first end to the second end, the downstream flow of the cooling air flowing in the axial direction and passing over the outwardly disposed side of each cooling ring of the plurality of cooling rings,
wherein the plurality of film holes are configured to enable the continuous cavity to communicate with the gas channel and the plurality of impingement holes are configured to enable the continuous cavity to communicate with the outside of the inner transition piece, such that the portion of the downstream flow of the cooling air flows from the outside of the inner transition piece to the gas channel through a series arrangement of the plurality of impingement holes, the continuous cavity, and the plurality of film holes,
wherein the cooling air having passed through the plurality of impingement holes but not having passed through the plurality of film holes passes through the continuous cavity by passing between the two axially facing sides of the three-sided structure and by not passing through either of the two axially facing sides of the three-sided structure,
wherein the plurality of cooling rings include a first cooling ring and a second cooling ring that are spaced apart from each other by a streamwise distance (L2) between a trailing side of the first cooling ring and a trailing side of the second cooling ring,
wherein the plurality of film holes include a first plurality of cooling ring holes arranged to correspond to the first cooling ring and a second plurality of cooling ring holes arranged to correspond to the second cooling ring, the first plurality of cooling ring holes having an effective cooling distance (L1) with respect to the second plurality of cooling ring holes, and
wherein the streamwise distance is substantially equal to the effective cooling distance.

### Claim 2 (depends on 1)

The transition piece according to claim 1, wherein a size of the plurality of impingement holes is larger than a size of the plurality of film holes.

### Claim 3 (depends on 2)

The transition piece according to claim 2, wherein the plurality of film holes is greater in number than the plurality of impingement holes.