Gas turbine engine compressors having optimized stall enhancement feature configurations and methods for the production thereof

Patent metadata

Field	Value
Publication number	US-11466694-B2
Application number	US-202016924887-A
Country	US
Kind code	B2
Filing date	Jul 9, 2020
Priority date	Feb 3, 2015
Publication date	Oct 11, 2022
Grant date	Oct 11, 2022

Abstract

Multistage gas turbine engine (GTE) compressors having optimized stall enhancement feature (SEF) configurations are provided, as are methods for the production thereof. The multistage GTE compressor includes a series of axial compressor stages each containing a rotor mounted to a shaft of a gas turbine engine. In one embodiment, the method includes the steps or processes of selecting a plurality of engine speeds distributed across an operational speed range of the gas turbine engine, identifying one or more stall limiting rotors at each of the selected engine speeds, establishing an SEF configuration in which SEFs are integrated into the multistage GTE compressor at selected locations corresponding to the stall limiting rotors, and producing the multistage GTE compressor in accordance with the optimized SEF configuration.

First claim

What is claimed is:

1. A multistage Gas Turbine Engine (GTE) compressor included in a gas turbine engine, the multistage GTE compressor comprising:
an engine casing;
a shaft mounted in the engine casing for rotation about a rotational axis;
a series of axial compressor stages, comprising:
a forward axial compressor stage containing a first rotor mounted to the shaft and surrounded by the engine casing; and
a first aft compressor stage containing a second rotor mounted to the shaft and surrounded by the engine casing;

a plurality of stall enhancing features (SEFs), comprising:
a first casing treatment feature comprising grooves formed in an interior of the engine casing disposed around the first rotor; and
an upstream injection feature positioned upstream of the second rotor within a flow field thereof, the upstream injection feature comprising a stator duct and conduit configured to direct pressurized airflow into a main flow path through the first aft compressor stage at a location proximate a hub of a stator immediately upstream from the second rotor.

2. The multistage GTE compressor of claim 1 , wherein the series of axial compressor stages further comprises a second aft compressor stage adjacent the first aft compressor stage, the second aft compressor stage containing a third rotor mounted to the shaft and surrounded by the engine casing; and
wherein the plurality of SEFs further comprises a SEF disposed around the third rotor.

3. The multistage GTE compressor of claim 2 , wherein the SEF is a second casing treatment feature comprising second grooves formed in the interior of the engine casing.

4. The multistage GTE compressor of claim 2 , wherein the multistage GTE compressor comprises leading and trailing axial compressor stages; and
wherein the forward axial compressor stage and the second aft compressor stage comprise the leading and trailing axial compressor stages, respectively.

5. The multistage GTE compressor of claim 1 , wherein the series of axial compressor stages further comprises:
a second forward axial compressor to which the plurality of SEFs is not applied; and
a second aft compressor stage to which the plurality of SEFs is not applied.

6. The multistage GTE compressor of claim 1 , wherein the grooves formed in the interior of the engine casing circumscribe the first rotor contained in the forward axial compressor stage.

7. The multistage GTE compressor of claim 1 , wherein the total number of rotors contained within the series of axial compressor stages is equal to n total , wherein the number of rotors including one of the plurality of SEFs is equal to n enhanced , and wherein 2<n enhanced <n total .

8. A multistage Gas Turbine Engine (GTE) compressor included in a gas turbine engine, the multistage GTE compressor comprising:
an engine casing;
a shaft mounted in the engine casing for rotation about a rotational axis;
a series of axial compressor stages, comprising:
a forward axial compressor stage containing a first rotor mounted to the shaft and surrounded by the engine casing; and
a first aft compressor stage containing a second rotor mounted to the shaft and surrounded by the engine casing;

a plurality of stall enhancing features (SEFs), comprising:
a first casing treatment feature comprising grooves formed in an interior of the engine casing disposed around the first rotor; and
a stator hub flow injection feature positioned upstream of the second rotor within a flow field thereof to direct pressurized airflow into a main flow path through the first aft compressor stage, the stator hub flow injection feature comprising a stator duct and conduit configured to direct the pressurized airflow at a location proximate a hub of a stator immediately upstream from the second rotor.

9. The multistage GTE compressor of claim 8 , wherein the series of axial compressor stages further comprises a second aft compressor stage adjacent the first aft compressor stage, the second aft compressor stage containing a third rotor mounted to the shaft and surrounded by the engine casing; and
wherein the plurality of SEFs further comprises a second casing treatment feature comprising second grooves formed in the interior of the engine casing disposed around the third rotor.

10. The multistage GTE compressor of claim 9 , wherein the multistage GTE compressor comprises leading and trailing axial compressor stages; and
wherein the forward axial compressor stage and the second aft compressor stage comprise the leading and trailing axial compressor stages, respectively.

11. The multistage GTE compressor of claim 8 , wherein the series of axial compressor stages further comprises:
a second forward axial compressor to which the plurality of SEFs is not applied; and
a second aft compressor stage to which the plurality of SEFs is not applied.

12. The multistage GTE compressor of claim 8 , wherein the grooves formed in the interior of the engine casing circumscribe the first rotor contained in the forward axial compressor stage.

13. The multistage GTE compressor of claim 8 , wherein the total number of rotors contained within the series of axial compressor stages is equal to n total , wherein the number of rotors including one of the plurality of SEFs is equal to n enhanced , and wherein 2<n enhanced <n total .

Assignees

• Honeywell Int Inc

Inventors

• Reynolds Bruce David
• Nolcheff Nick

Classifications

• F04D29/321

  for axial flow compressors · CPC title

• F04D27/001

  Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring · CPC title

• F04D27/0261

  by varying driving speed · CPC title

• F05D2230/00

  Manufacture · CPC title

• F04D29/526

  Details of the casing section radially opposing blade tips (ducts F04D29/545) · CPC title