Dynamic sealing device for an aircraft turbomachine, comprising two rotors (3, 8) which are configured to rotate about the one same axis (A) and different speeds, the said rotors extending at least in part around one another and dynamic sealing means (14) being mounted between the said rotors, characterized in that:the said sealing means comprise annular rings (38) extending about the said axis, these rings being mounted with the ability to slide on a first (3) of the said rotors, in a radial direction with respect to the said axis, and being able to bear radially via their external periphery against a second (8) of the said rotors which at least partially surrounds the said first rotor, and in that it further comprises:oil discharge means comprising an annular cavity (44) formed in the said second rotor, the said annular cavity opening radially towards the inside in the vicinity of the said sealing means and being in fluidic communication with oil passage ports (45) formed in the bottom of the cavity and passing through the said second rotor.

A seal segment (11) includes a seal body having a plurality of laminated thin plate seal pieces (20), and a high-pressure side plate (23). The high-pressure side plate (23) includes an outer diameter side edge portion (23b) which is an outer edge portion in the radial direction (Dr) and extends in a circular are shape in the circumferential direction (Dc), an inner diameter side edge portion (23c) which is an inner edge portion in a radial direction (Dr) and extends in a circular arc shape in the circumferential direction (Dc), and a front edge portion (23d) which is an edge portion on a front side in the rotational direction (Bc). The high-pressure side plate (23) further includes a reinforcing portion (40) only in a region of the high-pressure side plate (23) on the front side in the rotational direction (Bc).

A seal segment (11) includes a seal body having a plurality of laminated thin plate seal pieces (20), and a high-pressure side plate (23). The high-pressure side plate (23) includes an outer diameter side edge portion (23b) which is an outer edge portion in the radial direction (Dr) and extends in a circular are shape in the circumferential direction (Dc), an inner diameter side edge portion (23c) which is an inner edge portion in a radial direction (Dr) and extends in a circular arc shape in the circumferential direction (Dc), and a front edge portion (23d) which is an edge portion on a front side in the rotational direction (Bc). The high-pressure side plate (23) further includes a reinforcing portion (40) only in a region of the high-pressure side plate (23) on the front side in the rotational direction (Bc).

A seal includes a seal body disposed about a seal axis and configured to be mounted to a first component at a second axial end of the seal body. The seal body includes an interior surface defining a seal gland circumferentially extending about the seal axis. A packing is disposed within the seal gland. A retaining ring is in communication with a second radial side of the packing and is disposed within the seal gland. A plurality of exciter springs are mounted to a second radial side of the retaining ring. The plurality of exciter springs are biased against the interior surface of the seal body and are configured to center the packing within the seal body. The packing is configured to receive a second component and form a seal interface between the packing and the second component. The seal body is configured to form a portion of a passage.

A seal includes a seal body disposed about a seal axis and configured to be mounted to a first component at a second axial end of the seal body. The seal body includes an interior surface defining a seal gland circumferentially extending about the seal axis. A packing is disposed within the seal gland. A retaining ring is in communication with a second radial side of the packing and is disposed within the seal gland. A plurality of exciter springs are mounted to a second radial side of the retaining ring. The plurality of exciter springs are biased against the interior surface of the seal body and are configured to center the packing within the seal body. The packing is configured to receive a second component and form a seal interface between the packing and the second component. The seal body is configured to form a portion of a passage.

A seal segment includes a retainer extending in a circumferential direction of a rotary shaft on an outer circumferential side of the rotary shaft; a first seal body which has a plurality of first thin plate seal pieces extending inward in a radial direction from the retainer and laminated in the circumferential direction; a high-pressure side plate; a low-pressure side plate; and a second seal body having a plurality of second thin plate seal pieces which are laminated at an end portion of the retainer in the circumferential direction, extend inward in the radial direction, and have fluttering resistance higher than the first thin plate seal piece. The high-pressure side plate and the low-pressure side plate cover at least a part of the second seal body in the circumferential direction.

A seal segment includes a retainer extending in a circumferential direction of a rotary shaft on an outer circumferential side of the rotary shaft; a first seal body which has a plurality of first thin plate seal pieces extending inward in a radial direction from the retainer and laminated in the circumferential direction; a high-pressure side plate; a low-pressure side plate; and a second seal body having a plurality of second thin plate seal pieces which are laminated at an end portion of the retainer in the circumferential direction, extend inward in the radial direction, and have fluttering resistance higher than the first thin plate seal piece. The high-pressure side plate and the low-pressure side plate cover at least a part of the second seal body in the circumferential direction.

The invention relates to a seal arrangement for sealing a radial gap between an inner first component (8) and an outer second component (15) which can be rotated in relation to each other, the first component (8) being rotatable about an axis of rotation and the second component (15) being arranged coaxially to the first component (8). The seal arrangement comprises: a dynamic seal part (14) connected to the first component (8); a static seal part (15) connected to the second component (15); a first labyrinth seal (1) formed by a gap between a first section of opposing surfaces of the dynamic seal part (14) and the static seal part (15); and a leaf seal (2) which is radially arranged inside the first labyrinth seal (1). The invention is characterised in that the seal arrangement comprises a dust protection cover (3) connected to the second component (15), which is arranged radially outside the first labyrinth seal (1).

The invention relates to a seal arrangement for sealing a radial gap between an inner first component (8) and an outer second component (15) which can be rotated in relation to each other, the first component (8) being rotatable about an axis of rotation and the second component (15) being arranged coaxially to the first component (8). The seal arrangement comprises: a dynamic seal part (14) connected to the first component (8); a static seal part (15) connected to the second component (15); a first labyrinth seal (1) formed by a gap between a first section of opposing surfaces of the dynamic seal part (14) and the static seal part (15); and a leaf seal (2) which is radially arranged inside the first labyrinth seal (1). The invention is characterised in that the seal arrangement comprises a dust protection cover (3) connected to the second component (15), which is arranged radially outside the first labyrinth seal (1).

Embodiments of the disclosure provide a seal strip for a seal assembly for a turbomachine. The seal strip includes a retaining portion for fixed coupling within a recess in a stationary component of the turbomachine. A plurality of leaf members extend from the retaining portion, and a slit extends between adjacent leaf members of the plurality of leaf members. Each leaf member includes a first stepped edge and an opposing, second stepped edge, and the first stepped edge and the second stepped edge of adjacent leaf members are configured to sealingly mesh in a mounted state of the seal strip in the turbomachine.