Granted Patent B2

US 12,735,990 · App. 19/005,597 · Granted Sep 15, 2026

Inventors: Sylvain Vignola (St-Basile Grand, CA); Gabrielle Lamarche (Saint-Roch de Richelieu, CA)

Assignee: Pratt & Whitney Canada Corp.

F01D11/006F01D5/3007F05D2220/32F05D2240/24F05D2240/30F05D2240/55

Abstract

Claims (47)

1 . A rotor stage for a gas turbine engine, comprising:

a first rotor blade (FRB) having an FRB airfoil, an FRB attachment section, an FRB neck section, and an FRB platform, wherein the FRB neck section extends radially between the FRB attachment section and the FRB airfoil and extends axially between an axially forward end and an axially aft end, wherein the FRB platform extends laterally outward from the FRB neck section, wherein an axial portion of the FRB platform extends axially outward from the axially forward end or the axially aft end, and wherein the FRB platform has an FRB platform inner radial surface, an FRB platform outer radial surface, and an FRB platform lateral edge surface extending between the FRB platform inner radial surface and the FRB platform outer radial surface;

a second rotor blade (SRB) having an SRB airfoil, an SRB attachment section, an SRB neck section, and an SRB platform, wherein the SRB neck section extends between the SRB attachment section and the SRB airfoil, wherein the SRB platform extends laterally outward from the SRB neck section, and wherein the SRB platform has an SRB platform inner radial surface, an SRB platform outer radial surface, and an SRB platform lateral edge surface extending between the SRB platform inner radial surface and the SRB platform outer radial surface;

a disk configured for rotation about a rotational axis, the disk having a forward axial end surface, an aft axial end surface, an outer radial surface that extends between the forward axial end surface and the aft axial end surface, a first disk slot configured to receive the FRB attachment section, and a second disk slot configured to receive the SRB attachment section, wherein the first disk slot and the second disk slot are circumferentially adjacent one another;

wherein the first rotor blade includes at least one first rib extending outwardly from the FRB platform inner radial surface, wherein the at least one first rib includes a first rib end surface; and

wherein the rotor stage is configurable in an assembled state and in the assembled state the FRB attachment section is fully received in the first disk slot, and the SRB attachment section is fully received in the second disk slot, and in the assembled state the FRB platform, the SRB platform, and the outer radial surface of the disk form at least one tab slot; and

a seal member that includes a central segment and an axial locator tab, wherein in the assembled state, the central segment is engaged with the at least one first rib and the at least one first rib locates the seal member relative to the FRB platform lateral edge surface and the SRB platform lateral edge surface, wherein the axial locator tab is disposed in the at least one tab slot and radially between the axial portion and the outer radial surface of the disk, and wherein the axial locator tab extends axially outward towards the axial portion to a distal end surface, the distal end surface visible in the assembled state between the FRB and the SRB at the axially forward end or between the FRB and SRB at the axially aft end.

2 . The rotor stage of claim 1 , wherein the at least one first rib includes a plurality of first ribs, and in the assembled state, the plurality of first ribs are disposed to engage with the central segment of the seal member.

3 . The rotor stage of claim 2 , wherein each rib of the plurality of first ribs includes a first end surface configured for engagement with the seal member.

4 . The rotor stage of claim 3 , wherein the first end surface of each rib of the plurality of first ribs is spaced apart from the FRB platform lateral edge surface.

5 . The rotor stage of claim 3 , wherein the first end surface of each rib of the plurality of first ribs converges from a distal peak surface toward the FRB platform lateral edge surface.

6 . The rotor stage of claim 1 , wherein the at least one first rib comprises a plurality of first ribs, a first of the plurality of first ribs extends outwardly from the FRB platform inner radial surface on a pressure side portion of the FRB platform, and a second of the plurality of first ribs extends outwardly from the FRB platform inner radial surface on a suction side portion of the FRB platform.

7 . The rotor stage of claim 1 , wherein the second rotor blade includes at least one second rib extending outwardly from the SRB platform inner radial surface, wherein the at least one second rib includes a second rib end surface.

8 . The rotor stage of claim 7 , wherein the at least one first rib includes a plurality of first ribs, and in the assembled state, the plurality of first ribs are disposed to engage with the central segment of the seal member; and

wherein the at least one second rib includes a plurality of second ribs, and in the assembled state, the plurality of second ribs are disposed to engage with the central segment of the seal member.

9 . The rotor stage of claim 8 , wherein a first of the plurality of first ribs extends outwardly from the FRB platform inner radial surface on a pressure side portion of the FRB platform, and second of the plurality of first ribs extends outwardly from the FRB platform inner radial surface on a suction side portion of the FRB platform; and

wherein a first of the plurality of second ribs extends outwardly from the SRB platform inner radial surface on a pressure side portion of the SRB platform, and a second of the plurality of second ribs extends outwardly from the SRB platform inner radial surface on a suction side portion of the SRB platform.

10 . The rotor stage of claim 9 , wherein the first and the second of the plurality of first ribs each include a first end surface configured for engagement with the seal member, and the first and the second of the plurality of second ribs each include a second end surface configured for engagement with the seal member.

11 . The rotor stage of claim 10 , wherein the first end surface of the first and the second of the plurality of first ribs is spaced apart from the FRB platform lateral edge surface, and wherein the second end surface of the first and the second of the plurality of second ribs is spaced apart from the SRB platform lateral edge surface.

12 . The rotor stage of claim 10 , wherein the first end surface of the first and the second of the plurality of first ribs converges from a first distal peak surface toward the FRB platform lateral edge surface, and the second end surface of the first and the second of the plurality of second ribs converges from a second distal peak surface toward the SRB platform lateral edge surface.

13 . The rotor stage of claim 1 , wherein the at least one tab slot extends axially outward towards the axial portion.

14 . The rotor stage of claim 1 , wherein in the assembled state the FRB platform, the SRB platform, and the outer radial surface of the disk form a platform channel extending laterally between the FRB inner radial surface and the FRB lateral edge surface or between the SRB inner radial surface and the SRB lateral edge surface, the platform channel extending axially to the axially forward end or the axially aft end, and the platform channel comprising the at least one tab slot.

15 . The rotor stage of claim 1 , wherein the central segment or the axial locator tab has a uniform cross-sectional geometry.

16 . A rotor blade, comprising:

an airfoil;

an attachment section;

a neck section that extends radially between the attachment section and the airfoil and extends axially between an axially forward end and an axially aft end; and

a platform that includes:

a suction side platform portion that extends laterally outward from the neck section, wherein the suction side platform portion (SSPP) includes an SSPP inner radial surface, an SSPP outer radial surface, and an SSPP lateral edge surface that extends between the SSPP inner radial surface and the SSPP outer radial surface;

a pressure side platform portion that extends laterally outward from the neck section, wherein the pressure side platform portion (PSPP) includes a PSPP inner radial surface, a PSPP outer radial surface, and a PSPP lateral edge surface that extends between the PSPP inner radial surface and the PSPP outer radial surface;

a platform channel extending laterally between the SSPP inner radial surface and the SSPP lateral edge surface or between the PSPP inner radial surface and the SSPP lateral edge surface, the platform channel extending axially to the axially forward end or the axially aft end, and the platform channel partially forming a tab slot; and

at least one first rib extending outwardly from the SSPP inner radial surface and at least one second rib extending outwardly from the PSPP inner radial surface;

wherein the at least one first rib includes a first rib end surface, and the at least one second rib includes a second rib end surface.

17 . The rotor blade of claim 16 , wherein the first end surface of the at least one first rib is spaced apart from the SSPP lateral edge surface, and the second end surface of the at least one second rib is spaced apart from the PSPP lateral edge surface.

18 . The rotor blade of claim 16 , wherein the first end surface of the at least one first rib converges from a first distal peak surface toward the SSPP lateral edge surface, and the second end surface of the at least one second rib converges from a second distal peak surface toward the PSPP lateral edge surface.

19 . A rotor stage for a gas turbine engine, comprising:

a rotor blade having an airfoil, an attachment section, a neck section, and a platform;

wherein the neck section extends radially between the attachment section and the airfoil and extends axially between an axially forward end and an axially aft end;

wherein the platform includes:

a suction side platform portion that extends laterally outward from the neck section, wherein the suction side platform portion (SSPP) includes an SSPP inner radial surface, an SSPP outer radial surface, and an SSPP lateral edge surface that extends between the SSPP inner radial surface and the SSPP outer radial surface;

a pressure side platform portion that extends laterally outward from the neck section, wherein the pressure side platform portion (PSPP) includes a PSPP inner radial surface, a PSPP outer radial surface, and a PSPP lateral edge surface that extends between the PSPP inner radial surface and the PSPP outer radial surface;

a platform channel extending laterally between the SSPP inner radial surface and the SSPP lateral edge surface or between the PSPP inner radial surface and the SSPP lateral edge surface, the platform channel extending axially to the axially forward end or the axially aft end, and the platform channel partially forming a tab slot; and

at least one first rib extending outwardly from the SSPP inner radial surface and at least one second rib extending outwardly from the PSPP inner radial surface;

wherein the at least one first rib includes a first rib end surface, and the at least one second rib includes a second rib end surface;

a disk configured for rotation about a rotational axis, the disk having a forward axial end surface, an aft axial end surface, an outer radial surface that extends between the forward axial end surface and the aft axial end surface, and a disk slot configured to receive the attachment section;

wherein the rotor stage is configurable in an assembled state and in the assembled state the attachment section is fully received in the disk slot; and

a seal member that includes a central segment and an axial locator tab, wherein in the assembled state, the central segment is (i) engaged with the at least one first rib and the at least one first rib locates the seal member relative to the SSPP lateral edge surface or (ii) engaged with the at least one second rib and the at least one second rib locates the seal member relative to the PSPP lateral edge surface.

Assignments (1)

Continuity (1)

References Cited (60)